Skip to main content

Advanced Abradables and Tip Coatings for Gas Turbines

Objective



Objectives and content

Gas turbine efficiency is significantly influenced by the pressure losses caused by the inevitable gap between the rotating turbine blades and the stator parts.
Because contact between rotor and stator cannot be completely avoided with a small gap, systems are designed to allow for some rubbing. Honeycombs or abradable MCrAlY stator coatings are normally used to minimize the wear of the rotor blades when rubbing occurs. But, more efficient solutions must be developed on modern engines, because both suffer temperature limitation and standard MCrAlY have usually poor abradability. For higher temperature and closer control of the gap, a thick thermal-barrier coating must be applied on the stator, but presently with no rub-tolerance.

To increase the abradability of the stator coating, its composition and structure can be modified, but such changes must be strictly limited with respect to the loss of erosion resistance.

The solution can then lie in the hardening of the rotating blade tip to permit the use of harder ceramic or metallic coatings on the stator with greater resistance to erosion. These systems typically consist, on the blade tip, of hard particles embedded in a softer metallic matrix.

In the present programme, it is therefore intended:
- to assess the present European solutions, standard or in development, for outer air seals and blade tips.
- to develop coated grits or new grits for the hardening of the blade tips, as well as to improve the matrix and the stator coating for long life systems.
- to optimize the most promising of these systems, that will be tested on development rigs and on engine.

The consortium includes several engine manufacturers, which are the potential users of the innovating solutions to be developed, companies having a large experience in the field of abradables and tip coatings
and non industrial partners involved in tribology and materials science.

Funding Scheme

CSC - Cost-sharing contracts

Coordinator

TURBOMECA SA
Address

64320 Bordes
France

Participants (7)

BMW Rolls-Royce GmbH - Aeroengines
Germany
Address
60-70,Hohemarkstraße
61402 Oberursel
Bundesanstalt für Materialforschung und Materialprüfung
Germany
Address
44-46,Unter Den Eichen
12203 Berlin
Ecole Centrale de Lyon
France
Address
Avenue Guy De Collongues 36
69131 Ecully
MTU Motoren- und Turbinen-Union München GmbH
Germany
Address
655,Dachauer Straße
80995 München
Poeton Coating Technology Ltd.
United Kingdom
Address
Brokenford Lane
SO49 9DY Southampton
Sulzer Innotec AG
Switzerland
Address
Hegifeldstrasse 16
8404 Winterthur
Techspace Aero SA
Belgium
Address
121,Route De Liers
4041 Milmort