23:232:232

23.2 Gears and spline couplings

23.2.1 Gears

Problems or failures at gears can, besides results of the drop out of the power transmission, also trigger dangerous loads at other components. Does it come to the disruption of the power transfer, at least the outage of the function of following components/equipmaent (e.g. control units, generators, stators, pumps), must be expected. With thisA; the chance of an engine shut/failure down exists. Develop fragments (e.g., of teeth), the likeliness is given, that these get between the gear wheels in the failure region or neighbouring gears and trigger there extensive secondary failures.
Even if it doesn't come to an outage, seemingly little damages can act dangerously through the service or other influences (e.g., assembly, production). To these belong exitations of vibrations, which also act over long distances (Ill. 23.2.1-11). Here especially the, for the aeroengine operation, typical high-speed rotation becomes noticeable. Therefore problems concentrate, in contrast to the common engineering, rather on fatigue processes as at overloads by shocks (forced cracks, forced fractures) and high transferring torques with a penetration of the oil film at the tooth flanks (seizing/galling).
Gear failures and/or failures in causative connection with gears, demand targeted and effective remedies. Precondition is an identification of the failure mechanism and its causes as certain as possible. The experience shows, that for this, at gears are better chances as for anti friction bearings. In contrast to these the likelihood is less, that the failure origin is no more analyzable due to a damage by a pass on process or overheating with plastic deformations. Not less that is caused from primary fracture surfaces which are in an analzable condition. This is often the cause, when the fragment has been centrifuged, or if there are not yet fractured primary cracks.

Ill. 23.2.1-1 (Lit. 23.2.1-1 and Lit. 23.2.1-2): For propeller drives, planet gears are preferred. They must transfer high powers with lowest weight and smallest volume.
A special problem is the dissipation of the produced heat in gear wheels and bearings. Even best performance efficiency produces in the range of `upteen' KW during transferring high power. This problem will even icrease for future big geared fans. The heat must be discharged to the highest portion into the oil. The thermal and mechanical load of the oil demands special oil properties (Ill. 22.3.1-1). Even little disturbances of the oil flow can trigger catastrophic failures. Thereby the even load distribution at the planetary gear wheels is an especial challenge. It is crucial for the life of the teeth flanks and the bending stress at teeth the roots. For this it is necessary, to distribute the load equal on all planetray gears. This requirement can be achieved with features, which permit a self adjustment of the gear wheels. Therefore, depending from the design principle of the planetary gear, wheels on a carrier or engaged with a static geared ring (hollow wheel) are floating, respectively mounted by means of a hydrulic element. Failures of planetary gears are type specific, corresponding with the weak points. Anyway emerged failures can get instructional and point at highly loaded components. Also „minor“ failures like break outs of tooth edges, lead to extensive secondary failures if the fragments get between the gears.

Tooth fractures, influenced by the material at the flanks in the area of the pitch cicle, occur during typical high loads, caused by fatigue cracks. It should be mentioned, relatively big gear wheels of propeller gears are concerned. With the size, the required material homogenity and cleanness is a problem. The tooth flanks are usually surface hardened. So high strength can ve achieved ond compression stresses can be induced. This increases the fatigue strength. Do anyway fatigue cracks develop, they will start beneath the tooth flank (Ill. 23.2.1-5). In this case the cracss get first visible, when they exit to the surface. Then they have already the size, which triggers the short-term failing, caused from fast crack propagation to the critical crack length (forced fracture).

Failures by overload at planet wheels can be also the result of failures of the related bearings (Ill. 23.1.2-6). Then these failures are rather traced back at a changed engagement, as at forced fractures.
Weak points with the danger of fatigue are, be also bores of the oil supply.

Lightning strike is a typical danger for the deterioration of planet gear wheels from turboprop aeroengines (volume 1, Ill. 5.1.3-4). Here the blade tips of the propeller are the favored strike area (volume 1, Ill. 5.1.3-3 ). During circuit continuity, small arcs can develop. Concerned are the the tooth flanks, because they are separated by an electrical insulating lubricant film, comparable anti friction bearings (Ill. 23.1.1-21). Weld puddles develop with notch effect, changes of the material structure (embrittlement, drop of strength) and bell mouths (local load transmission). They form a weak point which triggers a fatigue fracture.
For this reason, if there is the suspicion of a lightning strike the instructions of the manual must be strictly complied. Mostly these go up to the diassembly of the gear and the visual check of potential affected components. To these primarily belong gear wheels. Not only their tooth flanks are suspect. At planet gear wheels, also the races of the bearings (anti friction bearings, friction bearings) must be checked most exactly for damages from a lightning strike.

Ill. 23.2.1-2.1 (Lit. 23.2.1-3, Lit. 23.2-4 and Lit. 23.2.1-5): Gears of aeroengines are accordant of the top of the gear technology of its time. the requirements for

  • transfer of high power,
  • high rotation speed,
  • small volumes and
  • low weight

Usually the toothing is case hardened. For very high circumferential speeds and low transmission torques the teeth are nitrided.
For weight saving at gearshafts the inner rings of the bearings can be integrated (Ill. 23.2.1-3).

Gear boxes/casings consist of sand casting from aluminium alloys or magnesium alloys. These have disadvantages which however can be controlled.

  • Considerably different thermal expansions and elasticity (modulus of elasticity), compared with the gear wheels, complicate the exact adherence of the axis-centres of the gearshafts.
  • Low fatigue strength demands according low loads.
  • Because of the low static strength, the transfer of loads like at bolts and bearing seats must be carried out by steel inserts (volume 4, Ill. 16.2.1.7-6). This complicates the overhaul, because the inserts must be sufficient covered or removed before the paint stripping and etching processes.
  • Corrosion susceptibility, especially of magnesium alloys, demands appropriate protection (volume 1, Ill. 5.4.1.2-9 ).
  • The disposition of light metal alloys for porosity can require sealing measures (e.g., infiltration, volume 4, Ill. 15.2-9).

Primarily there are three applications of gears in aeroengines:

Accessory gear (sketch above) serves the drive of auxilary devices like generators, pumps (oil, fuel) and at older aeroengine types, the mechanical/hydraulic control unit. These gears are driven by bevel gears from a main shaft, usually the high pressure rotor (radialdrive). Contrary, through this connection the starting process can occur. In the accessory gear itself spur gears are used.

Gears for the power output (output side) serve at turbo thaft engines the power extraction. Typical example are smaller aeroengines for helicopters (sketches middle). At two shaft aeroengines they take the power over spur gears directly from the shaft of the power turbine. At single shaft engines there is usually a clutch between. Also the gear has often simultaneously the function of an accessory gear and drives the auxilary devices (Ill. 23.2.1-11).

Reduction gear at starters are highly loaded and use mainly a planet design (Lit. 23.2.1-3 and Lit. 23.2.1-4). They are covered in detail in Ill. 23.2.1-2.2.

Propeller gears, which are integrated in the aeroengine (sketch below), are covered in Ill. 23.2.1-1.

Ill. 23.2.1-2.2 (Lit. 23.2.1-5): The use of reduction gears at starters are designed for a relative short running time. This is for the start procedure, till the automatic de-clutching when the aeroengine ramps up autonomous. If the gear casing is not integrated into the oil system of the aeroengine, an oil change has to be carried out, according to the maintenance manual (Lit. 23.2.1-5). The `waste oil' must be controlled for unusual abrasive and chips. If the starter, as normally, is mouted near the gas producer also high surrounding temperatures must be expected.
The gears of starters/starter generators are exposed to especially demanding operation conditions.

  • Very high rotation speeds.
  • Often the lubrication is not optimal e.g. oiltemperature unfavourable.
  • Shocklike loads.
  • Danger of overspeed and continuous loading, caused by failing of the clutch function. Thereby the starter will be carried along by the aeroengine.
    • Failing of the valve from the pressure airsupply (Lit. 23.2.1-19) at devices with airturbine drives. The starter then contiues running without load (Lit. 23.2.1-19).


At malfunctions during decoupling (Lit. 23.2.1-20) or during stiffness of the rotor to drive (e.g., very cold surrounding temperatures, volume 1, Ill. 5.1.5-3.2), overload of the teeth flanks and according features must be expected. To these belong „gray staining” (Ill. 23.2,1-7), seizing/galling and overheating at the driven/loaded teeth flanks.
Gear wheel failures develop also from failing bearings (Lit. 23.2.1-20). Thereby the consequences are not only limited to a failing of the starter, respectively skipping of the starting process. If gear teeth fracture, fragments can penetrate the casing and trigger extensive secondary failures (Lit. 23.2.1-19). The location of the starter in the region of the accessory devices can

  • trigger electric disruptions and shorts.
  • If leaks of fuel and oil develop, the danger of fires exists (Lit. 23.2.1-20).

Ill. 23.2.1-3 (Lit.23.2.1-9): Gear wheels of the aeroengine technology are frequently designed as gearshafts with integrated shaft lugs. These take the function of bearing inner rings, sliding surfaces for oil selas and coupling spline toothings. At bolted versions, flange connections are used. These characteristics of the lightweight design, form potential weak points besides the usual problems of gears of the mechanical engineering.

The toothing can, besides the in Ill. 23.2.1-4 described load depending failures, hint at further failures.
Effect of foreign objects, mostly as secondary failures, if a fragment (e.g., of an oil jet or a seal) gets into the tooth engagement. This produces plastic deformations. Thereby often form metallic particles. In an extreme case, forced fractures of the teeth occur. The consequence is a catastrophic failure of the whole gear wheel. Symptomes and features of sucgh a failure are

  • noticeable vibrations,
  • Loss of oil at damaged seals,
  • metallic particles/chips in the oil.

Before the wheel fails catastrophic, a limited failure can be identified at deposits on magnetic plugs and filters (Ill. 22.3.3.1-2).

Particles in the lubrication oil (Ill. 22.3.3.1-4). Concerned are contaminations, which also trigger failures at anti friction bearings. These produce wear and fatigue pittings at the tooth flanks.
During oil shortage, because of the high circumferential speed, the direct danger of seizing/galling damages exists (Ill. 23.2.1-4), which in a short period of time, during heavy chip production, means the outage of the toothing.

Material problems in the tooting are rather seldom. Concerned are:

  • Grinding deteriorations (soft/overheated locations, cracks).
  • Faulty surface hardening (too thin/unfavourable hardness profile, deviations of the material structure).
  • For an inner crack formation by hydrogen embrittlement, especially small case hardened teeth with a small cross section are prone (Ill. 23.2.1-14, volume 1, Ill. 5.4.4.2-3).
  • Contaminations/inhomogenities of the material. This danger rises with the size of the wheel (e.g., propeller gears) and the load.

Region of the geared rim: The lightweight design of gear wheels from aeroengines causes thin cross sections. This means for the membrane and the rim a very low stiffness. Such a disk shaped structure is extremely susceptible for disk vibrations (Ill. 23.2.1-9). In such a case the rim can perform an axial bending vibration. Thereby the outer edges at the tooth root are dynamically so high loaded, that fatigue cracks develop. Do these propagate far enough into the rim, the break out of whole segments, up to the separating of the whole rim occurs.
In the region of the gear rim caused by the production stress corrocsion cracking (SCC) can develop. It is about so called „burnishing cracks“ (volume 1, Ill. 5.4.2.2-4 and volume 4, Ill. 16.2.1.8.3-11). This danger exists especially, when these zones have not been at all or not sufficient shot peened.
Further problems are grinding failures and hardening failures (too soft, too hard, crack formation, high internal tension stresses).

Vibration wear (fretting) in grooves of damping rings: To damp vibrations in the appropriate area in the inner side of a rim, a circimferential groove is applied. In it a slotted springy ring (damping ring) is introduced which is pressured by the centrifugal force (volume 2, Ill. 7.2.3-7). The cross section of this rings can be square (piston ring) or circular (wire ring). Necessary for the function are friction movements against the wheel respectively the nut/groove. Thereby markedly wear is possibly at the ring and/or the the groove.

Weel membrane: Mostly fatigue cracks are concerned. They can develop during dynamic oveload with unusual heavy membran vibrations. Typical causes are

  • unfavourable engagement conditions,
  • damages of the toothing or
  • failing of the damping.

Production caused failures from which fatigue cracks start are

  • burnishing cracks,
  • cracks by hydrogen embrittlement,
  • Welding failures (Ill. 23.2.1-16, volume 4, Ill. 16.2.1.3-32).
  • Hardening failures (e.g., soft areas, crack formation, internal tensile stresses).


Bearing supporting shaft attachments can be formed as welded joined integral bearing rings or as bearing seats. The race of integrated bearing seats underlay the failure mechanisms of anti friction bearing inner rings (chapter 23.1.1). With convenient design and arrangement from experience, the weldseam (electron beam welding, friction welding, volume 4, Ill. 16.2.1.3-32) is sufficient fail-proof. At slided on inner rings, with an unsufficient tight seat and/or too large elastic deformation of the shaft (e.g., bending), fretting wear and loosening is possible.
Sliding surfaces of shaft seal rings run in by wear (form a groove) during long operation times. This indeed influences the function acceptable, however demands a repair during overhaul. Usually the sliding surface will be grinded (Ill. 23.4.2.1-2), coated/plated (hard chromium) and dimensional ground. Is the surface befor the chrome plating not sufficient shot peened, the danger of burnishing cracks (stress corrosion cracking=SCC) below the chromium layer in the base material exists (volume 4, Ill. 16.2.1.8-3).

Spline toothings are usually located at gear wheels in der hollow shaft. During unsufficient lubrication and(or too large vibration movements, they can wear in a so heavy, that failing/overrun occurres (Ill. 23.2.2-1 and Ill. 23.2.2-2).
Are the gear wheels burnished, the danger exists, that cracks develop by SCC in the serrations of the spline toothing. Then a sufficient certain non destructive proof is no more possible. This applies also the usual penetrant inspection or magnetic testing, used at gear wheels.

Ill. 23.2.1-4 (Lit. 23.2.1-6 and Lit. 23.2.1-15): At the teeth of gears different failures, respectively failure mechnisms can occur. They can be specified as component specific load limits. For this a diagram serves, in which the threshold torque versus the circumferential speed is shown.

The pitting threshold rises with the strength of the tooth flank. Pittings are fatigue break outs in the contact zone, i.e. at the pitch circle (detail right, Ill. 23.2.1-5). They can be compared with the race fatigue at anti friction bearings (Ill. 23.1.1-4). The pitting threshold is basis of the gear wheel life time. It rises with the circumferential, respectively the relative speed of the tooth flanks, in the region of the load transfer. The reason is a bearing and separating lubrication film. It forms during sufficient high sliding velocities and enables an EHL (elastohydrodynamic lubrication , Ill. 23.1.1-6).


The wear threshold is in the region of low circumferential velocities. It comes to mixed friction with metallic contact and abrasion. The threshold torque, from which a failure occurs, rises after a minimum steep with the circumferential velocity. This may be seen in connection with the formation of a favourable sliding film. The wear threshold may only be important during run-up, because of the typical high circumferential speeds of the gear wheels in aeroengines (e.g., start). A deterioration takes place above the pitch circle (detail left).

The threshold of seizing/galling is established at high torques and high circumverential speeds. In this region the torque produces such high teeth forces, that the loading capacity of the lubrication film is no more sufficient. It will be penetrated and metallic contact at high relative velocities occurs. The consequence are locally weldings /seizures which are forced separated. Radial scratches/grooves form, which increase to the tooth tip (detail right). The failure mechanism explains, why the threshold torque drops significant with the circumferential speed.

The fracture threshold is reached, when the fatigue limit of the tooth is surpassed (Ill. 23.2.1-5). Critical load is the pulsating tooth bending. The crack plane is located near the root, depending from the tooth geometry and strength (detail right). It drops only slight with the circumferential speed and determines for relevant operation speeds the threshold torque of gear wheels with hardened toothing. A failing by forced fracture occurs from unusual high loads during secondary failures. Thereby it can be about foreign object damage (FOD, OOD), shocklike loads and extreme torques (e.g., after bearing failures).


„Grey staining” (Lit. 23.2.1-21) is a fatigue failure in the surface region (Ill. 23.2.1-5). It was first about 1975 conciously identified at case hardened, ground tooth wheels of turbo gears. A generally usable certain calculation is obviously yet outstanding. Grey staining develops during mixed friction at the tooth flanks. Will the fatigue limit (under pulsating stresses) be surpassed at the roughness tips by a metallic contact, the development of micro pittings will occur and with this the grey staining. Especially endangered are the flank regions with negative slippage below the pitch circle. Typical is a grey zone with wear (scour), which begins in the root region and grows to the pitch circle. Microscopic (SEM) the surface is cliffy with axial oriented micro deteriorations (mikcro pittings). Gray staining is governed of several, connected influences.

  • Oil composition/condition.
  • Flank roughness.
  • Toothing geometry.

Ill. 23.2.1-5 (Lit. 23.2.1-9 and Lit. 23.2.1-10): The so called „pitting formation“ is at high-speed gears of the aeroengine technology the life determinant factor. Concerned is vibration fatigue of the tooth flanks. It is compearable with fatigue cracks and fatigue out breaks/pittings at the race tracks of anti friction bearings (Ill. 23.1.1-4). Independent, if due to load a crack starts from the surface or beneath, the crack growth accelerates if surrounding air and lubricant have access. Supporting acts the pumpeffect of the crack during the load cycles. Thereby act several effects which will be later discussed in the illustration text.

Failure modes: In most cases the pitting formation begins first at the driving wheel (bevel). The favoured position of the fatigue cracks usually is located in the region of negative slippage. Here the circumferential speed by the slippage is lower as at the mating wheel. This condition exists nearer the tooth root (sketch below). There the cracks begin shallow and deepen accelerating to the pitch circle. Usual are several parallel orientated cracks (sketch above).
At case hardenings, as they are usual at toothings in the aeroengine technology, form large-scale connected pittings. This can be explained with the failing of the less strength from the base material in the area of the detached hardening layer, after the beak out of a pit. At a case hardening, the bottom of the pit is heavily cliffed. Here, microscopically, firmly sticking beads with a smooth surface and the chemical composition of the base material, can be observed (Ill. 22.3.3.1-5). It is under consideration, if these develop by dispersing inside the crack, or if these are slugs from locally „temperature flashes”. Are such beads found in the oil, they are a hint at an advanced fatigue process in the pitch surface.
The vibration load gets failure effective with the periodic tooth load during every wheel turn.Two types of stresses develop from the friction forces between the tooth flanks. A shear stress and the hertzian stress. They codetermine, if the cracks start directly from the contact surface or below. For the forces, the lubrication conditions and the relative movements between the tooth flanks play the essential role.
The decline of the crack relatively to the tooth flank is similar to the race surfaces of the anti friction bearings (Ill. 23.1.1-3), determined from the relation of friction forces/shear forces and compression forces.
At high relative velocity between the load transferring tooth flanks, the separating lubricant film can induce overloading tensile stresses. These can surpass the fatigue strength of the tooth flanks in the micro region (see `grey staining', Ill. 23.2.1-4 and Ill. 23.2.1-4.1). The pressure distribution in the lubrication gap is very different, similar to a friction bearing. Thereby the hydraulic pressure, especially for high speed gear wheels can locally drop as far, that cavitation occurres (volume 1, Ill. 5.3.1-11.2). This reinforces the fatigue deteriotration process. With the mechanical loads, further effects act: During the fatigue process the metal is activated and oxidises increasingly. So obviously oxide nests can form below the surface (inner oxidation).
In connection with aging processes in the lubricant (Ill. 22.3.2-3.1) and/or from contaminations like water (Ill. 22.3.3.2.1-1), hydrogen can develop and diffuse into the material (volume 1, Ill. 5.4.4.1-3). A thereby developing embrittling effect can also promote the crack formation.


Influences at the pitting formation:

  • Crucial is the fatigue strength in the region of the tooth flanks. This depends decisive from the homogenity (fine material structure) and cleanliness of the material. An essential influence has the heat treatment, expecially the surface hardening.
  • The internal stresses in hight and distribution act together with the operation determined stresses. So the resulting stress can vary as well in height as also in distribution. To aspire are compression stresses. These can be obtained with a surface hardening like the case hardening (Ill. 23.2.1-6) and/or with shot peening (volume 4, Ill. 16.2.1.6-5 and Ill. 16.2.2.4-11).

In the lubrication gap, friction heat develops. It heats locally the tooth flank. Thereby, near the surface, thermal stresses arise.

Toothing properties and service conditions are important for the behaviour.

  • The design conforming tooth form influences by the conditions in the lubrication gap the load transfer.
  • The dimensional accuracy of the tooth geometrry decides about the bearing surface. Correlates this rather a point contact rises the maximum stress and approaches the surface.
  • The surface quality of the tooth flanks essential influences processes in the lubrication gap. A higher roughness promotes mixed friction and with this deteriorating peak stresses in the micro region (Ill. 23.2.1-4 and Ill. 23.1.1-8). This applies especially for start procedures and unfavourable oil condition (high temperature, decreasing bearing capacity, contamination with water etc.). With With lower roughness the pitting formation also decreases.
  • Service conditions act indirectly at the material loading through the lubrication condition. A higher load acts in two ways unfavourable. The forces at the tooth increase and the lubrication gap gets tighter.

A rise in the rotation speed respectively the circumferential speed triggers counter effects: Positive is, that the lubrication film becomes thicker. Besides this heat is produced. With this the temperature in the lubricant film rises. This lowers the viscosity and so its bearing capacity, the lubrication film gets thinner.

  • The lubrication oil influences the pitting formation through the processes in the lubrication gap. The relevant maximum shear stress in the tooth flank decreases first with a growing film thickness (up to about 5µ), but then markedly rises. This optimal, design according viscosity and with this thickness of the lubrication film, should aspired for the elasto hydrodynamic lubrication condition (EHL).

Additives in the oil (Ill. 23.1.1-6 and Ill. 23.1.1-7) can have a considerably effect at the pitting formation. Especially important for gear wheels are chemically acting

  • extreme-pressure (EP-) components,
  • Wear decreasing additions (anti-wear = AW).

These can act absolutely different at the wear. They react with the material of the tooth flanks and enable a controlled abrasion. i.e. they improve the surface finish.

Ill. 23.2.1-6 ( Lit. 23.2.1-2 and Lit. 23.2.1-15): At surface hardened gear wheels (case hardened, nitrided) frequently can be observed during vibrtion fatigue the crack origin below the hardening zone. Below the flank surface, thereby play non metallic inclusions as weak points (imperfections, inside the specifications) or flaws a crucial roll. They are limited from the specified and to be kept degree of purity. This complies reasonable with the sufficient safe limit of the non destructive testing method. Less safe is a failure limitation by monitoring the rough material production.
Appear at several, especially neighboured teeth fatigue cracks, then this indicates a high service load as main cause. In such a case in the crack origin rather weak points than failures are to expect.

There are soft inclusions (e.g., manganese sulfides) with low nothch effect and hard/brittle inclusions (e.g., aluminium oxide/alumina) with high notch effect. Also internal stresses, which form during the heat treatment as effect at the fatigue crack initiation must not be neglected. They arise because of different thermal expansion of the matrix from the base material aroud the inclusions.
An important influence at the development of inner cracks obviously has hydrogen. It can be supposed, that it forms during the diffusion in the case hardening process or nitriding and gets so into the material. The compression stresses in the case hardening layer hinder the escape by diffusion, respectively make a desembrittlement more difficult. Hard particles (e.g., carbides or aluminium oxide in mitriding steels) with high notch effect widen the lattice under tensile stresses in the inner of the tooth. Here the hydrogen diffuses and recombines. Over longer operation times, inner brittle cracks occur. At the beginning, this zone with typical micro features for hydrogen embrittlement (volume 1, Ill. 5.4.4.1-2), is positioned concentric around the origin (Ill. 23.2.1-14). Gear wheels in aeroengines, with typical small/slim teeth, are especially predestined for such failures. This can be explained with, for a stress balance necessary, high tension stresses in the inner. For this the relative thick compression zone of the hardnening layer is responsible. Typically the incipient cracks are located in the inner of the tooth cross section near the neutral fibre/axis. This excludes a too high operation load (bending stresses) as cause.

Ill. 23.2.1-7 (Lit. 23.2.1-8): In this schema and in the following text typical failure types/modes at tooth wheels are discussed. The failure appearance is shown in the illustrations 23.2.1-8.1, 23.2.1-8.2, 23.2.1-8.3.

Tooth fracture failures: Fractures of the whole tooth in the root area lead in the most cases to extensive secondary failures. Than a failing of the whole gear must be expected. In contrast break-outs at the tooth edges or spallings at the tooth tip trigger rather no spontaneous failing.
Forced fractures are mostly secondary failures from damages and/or overload. They develop through foreign objects between engaged teeth. Typical are features of a bending overload. The fracture surface of high strength materials mostly appears brittle. However, if not embritled, it is micro ductile (microscopical provable in the SEM). There are shear planes at the component surface. Surface hardenings (case hardening, case nitriding) can emerge at the fracture surface.

Fatigue fractures (HCF, LCF) usually show a macroscopic pronounced structure with arclike, concentric to the fracture origin positioned beach marks (lines of rest). The residual fracture then occurres as forced fracture, mostly with pronounced shear planes to the surface. The relation of the residual fracture surface to the fatigue crack area permits an estimation of the load of the gear wheel. Dark discoloured zones of the fatigue fracture are caused by fretting wear (`friction rust') and/or oil residues. The crack origin usually is located at the surface of the tension side of the bending loaded tooth. However there are cases, where the fatigue fracture starts from a flaw, respectively incipient crack (hydrogen embrittlement, Ill. 23.2.1-14) far inside the cross section of the tooth. In this case the crack may develop accelerating in the direction of the tensile zone, i.e. the loaded tooth flank.

Pittings are pit like break-outs on the bearing tooth flanks (Ill. 23.2.1-4). Mostly they are located beneath the pitch cycle. Running-in pittings (see `grey staining') develop in contact zones of mixed friction („hard bearing areas“) after the first bringing into service. The usual running-in wear leads to an even bearing of the flanks. After this process running-in pittings increase no more.
In this connection the, frequently in the specialist literature so called `grey staining' must be mentioned („micropittings”, Lit. 23.2.1-17). Concerned are grey appearing zones. Mostly these proceed over the width of the contact area and are displaced to the tooth root. Mikroscopically these can be identified as fatigue caused tiny break-outs. Preferred they appear in case hardened tooth flanks during loads below the formation of macroscopic fatigue break-outs. With this mechanism correlates the mechanism of the running-in pittings on race tracks of anti friction bearings (Ill. 23.1.1-7). Grey staining is promoted by

  • high load,
  • high slippage velocity/circumferential speed,
  • unsufficient bearing capacity of the oil film.

These conditions are rather to expect in highly loaded starter gears (e.g., planetary gears, Ill. 23.2.1-2.2).
Proceeding pitting formation decreases the bearing flank area and so increases the flank load. Additionally it means a dangerous notch effect. Both influences favor fatigue fractures.

Flank peelings, flakings appear at surface hardened teeth. Gas nitrided gear wheels show, instead pronounced pitting formation, a peeling of the tooth flank. Rather there can be found sharp edged splinterings. Gas nitriding layers wear with gradings up to about 10µm by overloading or vibrations. These also lead to ripplet flank wear, transverse to the direction of sliding/slippage, e.g. in radial direction.


Case hardenings and induction hardenings get a spill like appearance.
Wear is named as normal, if merely a smoothening of the tooth flanks occurs. Cause is the removal of roughness tips during mixed friction. Heavy wear is called, if already the tooth flange geometry is markedly changed. It develops during lubricant shortage or unsuitable lubricant.

Grinding wear forms under the acting of hard abrasive particles in the oil.

Seizing/galling: The initial stage shows scratches in the direction of the sliding movement. Does it come to a halt, we speak of `running-in seizing'. The grooves in the range of 10 µ depth form. In the final stage streaky roughenings develop. At first tooth root or tooth tip are concerned, because in the region of the pitch cycle the lubrication film forms best.
Plastic deformations can be observed during high overload e.g., a shock load or extreme gear vibrations (flutter). The failure mode are rippled deformations of the tooth flanks. Thereby often form burrs at the tip and the faces surfaces.
Surface cracks, as far these arn't production caused (hardening cracks, grinding cracks), form during overload with plastic deformations of a surface hardening.

Annealing can be traced back to extreme heat production (oil deficiency, overload). The toothening shows annealing colours (mostly blue). The hardness has dropped. Frequently seizing and plastic deformations can be observed.
These annealing colours must not be confused with production caused usual discolourations of gas nitriding layers.

Corrosion arises during storage with unsufficient corrosion protection. Rusting will occur. Vibrations during stand still produce fretting corrosion with the development of puce stains (Ill. 23.1.1-12). Here oxygen from the atmosphre and/or condensate acts. This is supported from the air expansion cycles during temperature changes. This produces o pump effect in the gearbox.
Electrical continuity (lightning) during operation, produces in a very short period of time small weld puddles like at anti friction bearings (Ill. 23.1.1-21). Over a longer period of time, e.g., during a short in the generator (Ill. 23.1.2-2), circuit conttinuity leaves at the loaded flank a broad zone similar to sandblasting („frosting“, Ill. 23.1.1-24). This consists of many microscopic small craters. Overheating features like `recast layer' and drop of hardness in the deterorated zone ensure the confirmation.

Cavitation also produces zones which appear like sand blasted and can be easy confused with electrical continuit. It can also arise at the unloaded flank. Microskopical (SEM) a differentiation is possible because the bottom of cavitation pits is more smooth. Also the deteriorated zone shows no features of overheating. In the final stage, the toothing will be damaged from abrasion.

Ill. 23.2.1-8.1, 23.2.1-8.2, 23.2.1-8.3 (Lit. 23.2.1-8 and Lit. 23.2.1-11 up to -13): In these illustrations it is attempted to enable the practitioner a first evaluation of toothening failures. An exact description of failures contain Ill. 23.2.1-4 and Ill. 23.2.1-5. So the understanding of informations in the overhaul manual and specifications should be easier. In cases of doubt, basically an expert, respectively the OEM should be consulted and approached according to the instructions.






Ill. 23.2.1-9 (Lit. 23.2.1-2, Lit. 23.2.1-8, Lit. 23.2.1-9 and Lit. 23.2.1-15): The sketches show typical tooth contact patterns at spur-toothed and skew gears. The upper half of the sketches shows the aktive flank (loaded flank). The sketches below shows, respectively the rear side. The counter wheel is supposed accurate. Contact patterns are itself no failure/damage. They develop on the tooth flanks in the region of the engagement, i.e. normally around the pitch cycle. The contact track usually appears bright because of micro deformations of the roughness tips. Exists an initial deterioration, similar running-in pittings (grey staining, Ill. 23.2.1-7), this can appear dull. Contact patterns can allow important conclusions in the context of problem analysis.

Typical causes for contact patterns which deviate from the optimum:

  • Differences in heat expansion between casing (light metal) and gear wheels (steel). Thereby a change of the centre distance or the alignment of the gear shafts can become appearent.
  • Elastic deformations of the light metal casing because of the low stiffness (modulus of elasticty/Youngs modulus).
  • Elastic bending of gear shafts by unbalances or under high transfer torques. Thereby the one-sided acting force at the gear rim becomes noticeable.
  • Unsymmetrical force application by a worn spline toothing of the shaft coupling (Ill. 23.2.2-3).
  • Assembly depending problems like the local damage of tooth flanks. Bending of the shaft during the axial push together of the toothening (Ill. .2.1-17).
  • Loosening of screw joints (fretting) from a wheel with flange-mounted shaft.
  • Production failure as dimension fault and geometry deviations. From experience, such causes are in the aeroengine engineering rather unlikely.
  • Vibrations which run relatively to the gear wheel and lead to a markedly deflection of the rim. They are either the result of unusual heavy exitation and/or the breakdown of the damping ring, e.g., the fracture of the damper ring (Ill. 23.2.1-10).


Faulty contact patterns caused from seemingly minor deviations, can trigger in the high speed accessory gears dangerous vibrations (toroidal modes, disc modes). The tooth frequency is very high and reaches the ultrasonig range. Accordingly high are the resonance frequencies which can be excited. Concerned are vibrations of higher modes (Ill. 23.2.1-10). This causes, that already tiny deflections correlate dangerous high vibration stresses (volume 3, Ill. 12.6.3.1-7).

Gear vibrations can proceed through several gear chains. So in seemingly independent components, especially in the region of accessory gears, failures can be triggered (Ill. 23.2.1-11). About this, here some examples:
Accessory devices:

  • Fatigue fractures at blades of turbopumps and rotors of blowers/compressors (Ill. 23.2.1-12).
  • Erratic electrical voltage of generators. Effect at elektronical devices like control units (Ill. 23.1.2-11).
  • Malfunctions of mechanical control units.
  • Increased vibration wear (fretting, Ill. 23.2.2-1) up to the separation of spline toothings of couplings from the drive shafts of the accessory devices (Ill. 23.2.2-3).
  • Fatigue fractures of components from the main shafts/rotors. Triggering of dangerous, high frequency disk vibration modes. Known are also cases, which can be brought in causative connection with the fracture of centric tension bolts (Ill. 23.2.1-11, volume 2, Ill. 6.3-3).
  • Fractures of shafts and gear wheels, caused by vibrations, which are induced through a power drain (Ill. 24-4).

Ill. 23.2.1-10 (Lit. 23.2.1-2): High speed gear wheels are extremely prone for vibrations. To control this, gear wheels are equipped with a friction damping. The location must be choosen at a suitable point, according the vibration mode which must be dampened (volume 2, Ill. 7.2.3-7 and Ill. 7.2.3-8). These are zones of the componet, where a relative movement as large as possible, between the wheel and the damping contact surface can be expected.(sketch below). Usually springy slotted rings in a circumferential groove are concerned (detail below).
So always first the failure causing vibration mode must be identified. This can be carried out by a test on a electro dynamic shaker at not too high frequiencies. Very high frequencies can afford special test setups like air sirens. Also the use of computers can be helpful. Criteria are the primary fatigue crack zones. Promising are thereby measurements of stresses with strain gauges. The evaluation of the exitation risks takes place with help of the so called Campbell Diagramms (volume 3, Ill. 12.6.3.4-1).
Gear wheel vibrations are usually, according to the tooth frequencies, very high frequency. This leads to high order modes of disk vibrations (several nodes, right sketch).
Especially at bevel gear hollow shafts, failures caused by vibration fatigue arose (sketch above left).
Dangerous gear wheel vibrations can be already triggered from very small irregularities in the engagement, during unsufficient damping. To this also belong damages from the assembly like tiny ridges at the tooth flanks (Ill. 23.2.1-12).
Dual tilted shafts are used at test rigs for the simulation of a power drain with the connection of auxilay drives from aeroengines in the fuselage of fighters. For this the shafts need interconnected flexible couplings. Fore example this can be cardan joints (Ill. 24-1.2) or couplings with a flexible intermediate member (rubber, sheet metal lamellas). Already during slight elbowing, angular accelerations during rotation can induce dangerous vibrations into the gear wheel system up to the accessory devices.

Ill. 23.2.1-11: The assembly technique of the centeric tension bolt from the gas producer turbine of this helicopter engine was changed seemingly without risk. With this it should be prevernted, that this touches the bore wall in the hub of the turbine wheel of the 1st gas producer stage. So strength decreasing fretting schould be avoided in this extremely high stressed zone. However, over years already no failure which had emerged, was triggered from fretting. Therefore this was a precaution measure. To prevent the touching, the tension bolt was more precise than usual centered during assembly of the rotor. After about one year in service with this change at several aeroengines occurred fatigue fractures in the tension bolt. An investigation showed as failure cause an extremely high frequency resonance vibration of the tension bolt (volume 2, Ill. 6.3-3). This had been possible, because the damping of the bolt failed due to the new assembly technique. Obviously the vibration was transfrered from the output gearbox through the shaft system. In one case a suboptimal contact pattern of a gear weel could be seen. This was caused from the assembly, but absolutely acceptable. At the former assembly technique, obviously the contact of tension bolt and turbine wheel damped unknowigly such inevitable exitations. After the reintroduction of the `old' assembly technology, no such failures occurred any more.
This example reveals, that also typical extremely high frequent vibrations orginating from the gear wheels can be transferred through the gear chains and shafts to remote regions. Even, when at the first sight, there is no connection.


Ill. 23.2.1-12: The oil cooler of a small gas turbine is feeded with the air from a blower. The used blower wheel has a diameter of about 12 cm and a rotation speed of about 20 000 r.p.m. The drive takes place with a chain of gears. The wheel consists of pressed thermosetting glass fibre reinforced resin. This material was choosen because of its high inner damping and good fatigue strength. Before, the wheels have been milled from a high strength aluminium alloy. Its blades suffered frequently fatigue fractures. After a longer time since the introduction of the reinforced plastic wheels, also a fracture occured. A segment from the bladed rim was centrifuged. The investigations allowed to conclude at a fatigue fracture.Vibration tests on an elektrodynamic exciter (shaker) pointed at an extremely strong vibration exitation with a very high frequuency. As probable vibration exitation, a small mechanical produced bulging at the flank edge of a gear wheel was identified (detail). It may be formed during an assembly, a few operation hours before.

This example gives an impression from the extremely intense vibration exitation, caused from a small nonuniformity respectively damage of a gear wheel.

Ill. 23.2.1-13: It shows the apparance of a damage from a lightning strike (volume 1, Ill. 5.1.3-3 and Ill. 5.1.3-4). Remarkable is the coinciding position of the weld puddles, produced by the arc during the electric circuit at the neighboured teeth.

Ill. 23.2.1-14: After longer operation periods, (ca. 1000 hours) it came in several cases at the bevel gears of the radial drive (tower shaft) of the accessory gear to tooth fractures (sketch right). Get these fragments into the toothing, it came to dangerous failures with shut down of the aeroengine. The investigation showed, that fatigue fractures are concerned, which started fom an embrittled zone inside the tooth. The structure of the fracture at the incipient crack showed typical features of hydrogen embrittlement (volume 1, Ill. 5.4.4-2). The hydrogen diffuses into the material during the case hardening and lead over a long period of time to delayed crack formation. With sufficient crack size the fatigue crack occurred. As remedy all gear wheels are checked with a special ultrasonic testing during every overhaul. Thereby several cracks could be identified in time and the wheels scrapped.

Ill. 23.2.1-15: Burnishing cracks in gear wheels are known and formidable since long time. Concerned is a type of stress corrosion (causic embrittlement, volume 1, Ill. 5.4.2.2-4). Therfore, now some OEM forbid, at least during overhaul, the use of this process.
In the example above, it came to the cracking in the region of the inside located spline toothing (Ill. 23.2.1-3). From this, during service, a fatigue crack started. In the shown case it was identified due to vibrations, before the complete failure of the wheel. In other cases, the wheel fractured and separated the drive. The consequence was the overspeed of the gas producer with the fracture of the turbine wheel (volume 1, Ill. 5.4.2.2-4).
The example below shows the failure of a bevel gear to the radial shaft (tower shaft). In this case in the shaft accretion a fatigue crack started from a burnishing crack. Such burnishing cracks developed expecially frequent during overhaul. Concerned from the cracks have been ground and chromium plated wear surfaces (volume 4, Ill. 16.2.1.8-3). The burnishing cracks formed under the chromium layer. These have been sliding surfaces of the sealing lip from a radial seal ring (Ill. 23.4.2.1-2). A preventing protection against cracks is shot peening of the grinding surface before the chromium plating. The compression stresses protect the repair zone from the effect of the burnishing bath, which can penetrate through the typical cracks in the chromium layer to the base material.

Ill. 23.2.1-16: Welding joints at gear shafts (sketch left) are potential weak points. Therefore these are positioned, if possible, in less high loaded zones. The intense process monitoring and the non destructive testing from experience guarantees the quality. So with sufficient certainty, dangerous flaws can not get to the assembly. In the shown case, it came during the development phase to a fatigue crack at a flaw (incomplete fusion, detail) of the elektron beam weld in the disc membrane (volume 4, Ill. 16.2.1.3-32).


Ill. 23.2.1-17: The experience teaches, that obviously during the assembly of a gear, an increased risk of a dangerous damage of a gear wheel exists (bath tub curve). A critical phase exists, if gear wheels must be axially pushed for latching. Do thereby the faces of the tooth collide they can be damaged (sketch left). Above this, a high bending moment can plastically bend the shaft. In the shown case, at the accessory gear of the mounted aeroengine, assembly work was done. This took place at the drive shaft from the scavenge pump, mounted at the front of the aeroengine. Visibility and accessibility have been hindered during this work. During assembling of the cover together with the gearshaft it came to the contact of the gear faces. This was not noticed because the gear wheel was very slim. So, also the gap between cover and casing was not identified as unusual. The gap was closed with the tightening of the flange bolts. Thereby the filigree shaft was unnoticed bend, before the gear wheels „snapped in place”. During a flight, the shaft fracturend, corresponding the deformation with a onesided bending fatigue fracture. The fighter airplane was destroyed during emergency landing (Ill. 19.1.4-5.2). A failure investigation could clear the described cause. During an inspection of the airplanes with the same assembling process, sevreal further cases have been found. The bend shafts could be exchanged before failing.

Ill. 23.2.1-18 (Lit. 23.2.1-16): Gear pumps take a special position under the gears. Different to gears they seve the delivery of a fluid/liquid (oil or fuel). From experience these are extremely fail-proof components. However, they are endangered besides from function caused problems, especially from secondary failures. These are traced back to primary failures of other components. Thereby the oil system (Ill. 22.3-1) differs from the fuel system by a closed loop with a circulating medium (Ill. 22.2-18 and Ill. 22.2.2-3). So time dependent effects like aging, coke formation or wear can increase over the time and trigger „creeping failures“ in the pump. Even if filters and sieves can withhold dangerous foreign objects, still the danger exists during a disturbance of the oil flow. For example, if the pressure is lowered, cavitation damages can occur.

Rises the pressure behind the pump, accordingly increases the mechanical load. This can lead to ovreload failures. Typical short time effects are seizing/galling of the teeth flanks or LCF fatigue fractures at the tooth root. Long time effects are abrasion, forming of fatigue pits at the tooth flanks or HCF vibration fatigue.
The toothing is endangered from foreign objects. At sealing gaps and bearings a self-energizing failure by jamming during unacceptable heating can occur in very short time.

Ill. 23.2.1-19 (Lit. 23.2-18): Sensor data will be combined for analysis with vibration readings (mearuring of acceleration and frequency) in a computer based analysis (e.g., DPTOCC, Ill. 25.1-7). So, features of the gear due to design will be included. With this, informations about the conditions are possible. This enables conclusions at wear, fatigue and fracture. From the OEM specified limits decide about an exchange.
Besides vibration based analysis, further symptoms, expecially on site, can be evaluated from an experienced practitioner:

  • Oil leaks.
  • Traces of overheating.
  • Wear/damages (e.g., seals, multisplinetoothings, Ill. 23.2.2-1; tube clamps, Ill. 23.5.1-5).
  • Chips at magnetic plugs and sieves/filters.

References

23.2.1-1 L.Kerber, „Deutscher Start für eine sowjetische Triebwerksepoche, Das PTL-Triebwerk Kusnezow TW-2”, Zeitschrift „Fliegerrevue“, Edition 06, 1996, 6 pages.

23.2.1-2 C.Albrecht, J.Mack, „Drive System Technology Advancements”, Zeitschrift „Journal of the American Helicopter Society“, April 1981, page 18-24.

23.2.1-3 I.E.Traeger, „Aircraft Gas Turbine Engine Technology, Second Edition”, Verlag : Glencoe/McGraw-Hill 1994, ISBN 0-07-065158-2, page 307-321 and 559-562

23.2.1-4 „The Jet Engine“, Rolls-Royce.plc. 1986, 994, ISBN 0-902121-2-35, Ausgabe 1996, page 81 and 121-128.

23.2.1-5 M.J.Kroes, T.W.Wild, „Aircraft Powerplants, Seventh Edition”, Verlag : Glencoe/McGraw-Hill 1990, ISBN 0-02-801874-5, page 354, 367, 372, 470.

23.2.1-6 J.Broichhausen, „Schadenskunde, Analyse und Vemeidung von Schäden in Konstruktion, Fertigung und Betrieb“, Carl Hanser Verlag München, 1985, chapter 10.

23.2.1-7 T.E.Tallian, „Failure Atlas for Hertz Contact Machine Elements”, ASME Press, ISBN 0-7918-0008-3, 1992.

23.2.1-8 Allianz Versicherungs-AG, „Allianz-Handbuch der Schadenverhütung“, 3. Auflage, 1972, page 388-410.

23.2.1-9 V.Krüger, W.J.Bartz, „Untersuchungen des Einflusses moderner Schmierstoffe auf die Pittingbildung bei Wälz-und Gleitbeanspruchung”, Abschlussbericht, Forschungsheft 39 der Forschungsvereinigung Antriebstechnik e.V. 1976.

23.2.1-10 L.Engel, H.Klingele, „Rasterelektronenmikroskopische Untersuchungen von Metallschäden“, 2. Auflage, Carl Hanser Verlag München Wien 1982, ISBN 3-446-13416-6, 160,161, page 149-150, 158, 159.

23.2.1-11 H.Huppmann, „Aus Schäden Erfahrungen sammeln - Fehlerquellen und Fehlerstatistik, Übersicht über Schadensarten an Zahnrädern”, Zeitschrift „asr. Digest für angewandte Antriebstechnik“, Heft 1, April 1973, 1. Jahrgang, page 53-56.

23.2.1-12 P.Lynwander, „Gear Drives for Turbomachinery” in J.W.Sawyer, „Sawyer's Turbomachinery Maintenance Handbook“, First Edition, 3. Band, page 11-1 up to 11-22.

23.2.1-13 Metals Handbook Ninth Edition, „Volume 11 Failure Analysis and Prevention”, Verlag ASM, ISBN 0-871170-007-7, Kapitel von L.E.Alban„Failures of Gears“, page 586-601.

23.2.1-14 „Gear Design, Manufacturing and Inspection Manual, Design Guidelines for High-Capacity Bevel Gear Systems”, AE-15, SAE, page 112-121.

23.2.1-15 J.Holland, „Zur Schmierfilmausbildung bei Evolventenverzahnungen“, Zeitschrift „Schmiertechnik + Tribologie” 29. Jahrgang, 5/1982, page 195.

23.2.1-16 P.M.Farwell, „Vermeiden Sie Pumpenreparaturen“, Zeitschrift „ Fluid”, 6 Juli 1978, page 18-20.

23.2.1-17 Wikipedia, „Graufleckigkeit“, de.Wikipedia.org., Stand 27.05.2007, page 1.

23.2.1-18 W.Bartelmus, „Gearbox Diagnostics Fault Detection”, Zeitschrift „Maintenance World“, www.maintenanceworld.com, May 17, 2004, page 1-10.

23.2.1-19 Transportation Safety Board of Canada (TSB), „TSB Report Number A96o0125, Engine Fire”, 18. July 1996, page 1-3.

23.2.1-20 AAIB Bulletin No: 5/2002, Ref: EW/C2001/09/01, „ Allison AE3007A turbofan engine, starter failure“, 6.Sept. 2001, page 1-5.

23.2.1-21 J.Theißen, „ Graufleckenbildung an Zahnrädern - Ursachen, Prüfverfahren, Berechnung, Praxiserfahrungen”, www.ib24.de/images/ib-gregorius-PDF's/…/Vortragsmanuskript.pdf, page 1-21.

23.2.1-23 E.Bauer, „Beispiele für Verzahnungsschäden, ausgehend von innenliegenden Fehlstellen“, Zeitschrift „ Allianz Report” 68 (1995), Heft 6 , page 230-238.

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