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21.2.8 Regeneration by HIP (Hot Isostatic Pressing).

Hot isostatic pressing (HIP, Ill. 21.2.8-2) can be applied as a regeneration procedure for creep deteriorated hot parts. With it inner flaws like creep voids and micro cracks can be compressed and fused with a high outer gas pressure and at hitgh temperatures (Ill. 21.2.8-1).
The process is also applied at new parts for inner casting porosity (volume 4, Ill. 15.3-8 and Ill. 15.3-9), welding failures as well as diffusion welding processes (volume 4, Ill. 16.2.1.3-37 and Ill. 16.2.1.3-39) and repairs (welding, brazing).

The requirements for a „HIP regeneration“ exist by far not in all cases of operation deteriorated hot parts. Did alredy faults open to the surface, the closing is no more possible determined by the principle.

Illustration 21.2.8-1 (Lit. 21.2.8-3 and Lit. 21.2.8-4): Hot isostatic pressing (HIP) is a process at which parts are charged in an autoclave with gas under high pressure and material specific temperatures (Ill. 21.2.8-2 and volume 3, Ill. 12.5-18). Thereby closed faults to the outside (gastight) are plastically compressed. Are the surfaces of the separation/flaw sufficient clean, they fuse/sinter together. This effect can be used for the repair of parts with inner deteriorations/faults (creep).

The creep of hot parts usually develops with inner creep voids (volume 3, chapter12.5) and micro cracking. As long as no, open to the surface crack formation occures, the microscopic faults are free from oxides. They can completely disappear during the HIP process by diffusion welding/sintering. Unfortunately by far not all materials of hot parts show this type of deterioration under typocal operation conditions. Just the casting alloys of turbine blades and vanes show a significant less pronounced formation of creep voids than wrought alloys. Those can be found only at turbine blades of elder aeroengine types.

The high HIP temperature simultaneously acts as a heat treating. This can improve a material structre which has changed during operation (e.g., orientation and coarsening of the age hardening phase).

A HIP regeneration can be quite succeccessful and is applied in single cases (Ill. 21.2.8-3.1/-3.2). For turbine blades from a forging alloy the usable lifetime can be markedly extended with an acceptaple scatter (Lit. 21.2.8-1). However it was observed, that it must be reckoned with renewed accelerated initially creep (Ill. 21.2.8-3.2 and volume 3, Ill. 12.5-3), comparable with new parts.

But a HIP regeneration also retrieves potential risks:

  • Faults which are open to the surface can not be closed. This must be especially considered, if hollow parts are concerned. To those belong cooled turbine blades (Ill. 21.2.8-3.1). Here it must be reckoned with a crack formation in the cooling channels/bores by thermal fatigue (volume 3, Ill.12.6.2-9). Often this micro cracking can not be sufficient safe identified with NDT tests, suitable for series application.
  • Faults which are coated with reaction products, mostly thin oxide layers, allow no diffusion welding. This means, the flaw will be compressed but its detrimental effect remains.Naturally the application of the HIP process for regeneration must be approved by the OEM and the responsible authorities after sufficient proofs, respectively testing.

A further application of the HIP treatment during the repair process can follow the high temperature brazing of hot parts (chapter 21.2.2) or the repair welding. This can serve the closing of sufficient oxidation free pores, cracks and separations which are sealed from the joining to the surface.

Note: A regeneration by HIP can only be successful, if the deterioration (creep voids, micro cracking) is closed to the surface.

Illustration 21.2.8-2 (Lit. 21.2.8-3 and Lit. 21.2.8-4): This sketch shows the construction of a frequent HIP press type. There are such facilities with an inner diameter in the range of 10-cm up to a meter. The adjustable inner pressures can be markedly above 1000 bar and the temperatures fare above 1000°C. Naturally they must be adjusted at the particular application. With a suitable configuration, also a following accelerated coolig can be realised. The costly facility, together with the inert gas (argon) and the energy consumption, makes the process not cheap. Therefore for every case the rentability must be checked..

The evaporation of graphite from the heating can influence accessible surfaces of the parts. If there are concerns (carbonisation), a suitable cover (e.g., gas permeable container) is necessary.

Illustration 21.2.8-3.1 (Lit. 21.2.8-1 and Lit. 21.2.8-2): Concerned is a, since years successful series application of the HIP proscess for the regeneration of turbine rotorblades (sketch middle). In this case the operation lifetime is governed by a creep deterioration with the formation of voids (pores). With this forged blades are especially suited for the regeneration process. However the requirement is, that not yet unacceptable microcracks had formed in the region of the cooling air channels (detail below left). This is checked before the regeneration at six blades, equal distributed at the circumference. They will be destructive tested by metallography. Extensive experiences and investigations allow to use the creep void formation as a criterion for the regeneration ability (Ill. 21.2.8-3.2 and volume 3, Ill. 12.5-7).

Note:

For the evaluation of the lifetime governing creep damage, the plane of the metallographic cut must be positioned and correct orientated in the relevant cross section of the part.

Illustration 21.2.8-3.2 (Lit. 21.2.8-1): The upper diagram shows the typical creep void formation for the case in Ill. 21.2-3.1. The dependence from the operation time can be seen. Thereby the scatter is typically large. Therefore the ability for a regeneration needs a sufficient safety margin.

The diagram below shows test results at used blades without and with HIP regeneration. Typical for the regenerated blades is a pronounced primary creep and tertiary creep. At 75% of exhausted lifetime an extension of about 50% could be achieved. This would be sufficient for a further overhaul inverval. A drop of the fatigue strength (HCF) or a markedly embrittlement did not occur, although the age hardening phase differed from the new parts condition.

References

21.2.8-1 H.Huff, J.Wortmann, „Repair and Regeneration of Turbine Blades, Vanes and Discs”, Conference Proceedings AGARD-CP-317, „53rd Meeting of the AGARD Structures and Materials Panel“, Noordwijkerhout, the Netherlands, 27 September - 2 October 1981, page 13.1-13.7.

21.2.8-2 „Heiltherapie für Triebwerks-Leitschaufeln” (Hochtemperatur-Breitspaltlötverfahren), Zeitschrift „VDI Nachrichten“, Nr. 48 /29.November 1985.

21.2.8-3 K.L.Cheung, C.C.Leach, K.P.Willett, A.K.Koul, „Rejuvenation of used turbine blades by hot isostatic pressing and heat treatment”, Conference Proceedings AGARD-CP-317 , „53rd Meeting of the AGARD Structures and Materials Panel“, Noordwijkerhout, the Netherlands, 27 September - 2 October 1981, page 10.1-10.6.

21.2.8-4 W.J.van der Vet, „HIP-Process, Potentials and Applications”, Conference Proceedings AGARD-CP-317, „53rd Meeting of the AGARD Structures and Materials Panel“, Noordwijkerhout, the Netherlands, 27 September - 2 October 1981, page 11.1-11.16.

© 2021 ITTM & Axel Rossmann
21/212/2128/2128.txt · Last modified: 2020/06/25 22:43 (external edit)

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