WO2011009433A1

WO2011009433A1 - Abradable coating to be arranged on a gas turbine component

Info

Publication number: WO2011009433A1
Application number: PCT/DE2010/000810
Authority: WO
Inventors: André Werner; Michael Schober; Siegfried Sikorski
Original assignee: Mtu Aero Engines Gmbh
Priority date: 2009-07-21
Filing date: 2010-07-10
Publication date: 2011-01-27
Also published as: DE102009034025A1

Abstract

The invention relates to an abradable coating (10) to be arranged on a gas turbine component, especially an aircraft engine housing (12) or a segment thereof. The abradable coating (10) comprises an elastomer sealing member (14) that is to cooperate with another gas turbine component, in particular a rotor, which is disposed so as to be movable relative to the abradable coating. At least one reinforcement element (16) providing dimensional stability is embedded in the elastomer sealing member (14). The invention further relates to a turbomachine, in particular an aircraft engine, comprising a housing (12) on which an abradable coating (10) is arranged.

Description

The invention relates to an inlet lining of the type specified in the preamble of patent claim 1 for arrangement on a gas turbine component. The invention further relates to a turbomachine, in particular an aircraft engine, specified in the preamble of claim 8 type with a housing on which an inlet facing is arranged.

Such an inlet lining for arrangement on a gas turbine component, in particular an aircraft engine housing or an aircraft engine housing segment, is already known, for example, from DE 10 2007 053 135 A1. The inlet lining, which serves as part of a sealing system to increase the performance of a gas turbine, in this case comprises an elastomeric sealing body, preferably made of silicone, for cooperation with a rotor of the gas turbine that is movable relative to the inlet lining. The inlet lining is usually arranged on a housing acting as a stator of the gas turbine. The rotatably disposed within the housing rotor has a plurality of blades whose radially outer and possibly armored blade tips when moving the rotor strip the inlet lining and produce by material removal depressions in this inlet lining. As a result, the smallest possible radial gap between the rotor and the housing is achieved, which improves the aerodynamic properties of the gas turbine. The removal of material usually does not take place over the entire circumference of the inlet lining, but usually only sickle-shaped. The aim is always to minimize the aerodynamic flow through this radial gap and thus aerodynamic gap losses from a high-pressure side of the rotor blades to a low-pressure side in order to ensure high efficiency.

Object of the present invention is to provide an inlet lining, which allows an improved gap attitude. Another object of the invention is to provide a turbomachine with an improved gap attitude. The objects are achieved by an inlet lining with the features of claim 1 for placement on a gas turbine component and by a turbomachine with the features of claim 8. Advantageous embodiments with advantageous developments of the invention are specified in the dependent claims, wherein advantageous embodiments of the inlet lining are to be regarded as advantageous embodiments of the turbomachine and vice versa.

An inlet lining, which allows an improved gap attitude, according to the invention o created by the fact that in the elastomeric sealing body at least one shape-stabilizing

Reinforcement element is embedded. In contrast to the prior art, the reinforcing element prevents unnecessary damage to the elastomeric sealing body when tearing a rotor or the like on the inlet lining by tearing larger elastomer areas, cracking, overstretching beyond the nominal extent and the like. Here-5 through a reliable shape stabilization of the inlet lining or the elastomeric sealing body is ensured, whereby a more uniform abrasion, the improved gap attitude and a corresponding increase in efficiency of an associated gas turbine are ensured. At the same time, the reinforcing element advantageously increases the service life of the inlet lining. Instead of a single reinforcing element, two or more reinforcing elements may be provided.

In an advantageous embodiment of the invention, it is provided that the reinforcing element is at least partially honeycomb-shaped and / or fiber carpet-shaped and / or weave-shaped and / or jelly-shaped and / or Multiaxialgelegeförmig and / or braided 5 and / or mat-shaped and / or felt-shaped. As a result, the inlet lining can be structurally made particularly flexible in order to optimally take account of different geometries and requirement profiles. It can also be provided that the reinforcing element is uniform over the predominant and / or the entire extension region of the inlet lining.

0 Further advantages result from the reinforcing element inorganic reinforcing fibers, in particular basalt fibers and / or boron fibers and / or glass fibers and / or ceramic fibers and / or silica fibers, and / or metallic reinforcing fibers and / or organic reinforcing fibers, in particular aramid fibers and / or carbon fibers and or polyester fibers and / or nylon fibers and / or polyethylene fibers and / or polyacrylamide fibers. As a result, the elastomeric sealing body can be advantageously formed as a fiber-elastomer composite part with high specific stiffness and strength and is therefore ideal for lightweight applications. The respective mechanical and thermal properties of the inlet lining can be adjusted selectively over a variety of parameters such as the material combination reinforcing element-elastomer sealing body, fiber angle, fiber volume fraction, layer order and the like.

By virtue of the reinforcing element comprising flattened reinforcing fibers, in particular notch-sensitive fibers can be protected from damage during the production of the enema lining. Alternatively or additionally, the adhesion between the reinforcing element and the elastomeric sealing body can be considerably increased by an adhesion-promoting application. In a further advantageous embodiment of the invention, it is provided that the reinforcing element comprises short fibers and / or long fibers and / or continuous fibers and / or a wire. In this way, the mechanical properties of the inlet lining can be optimally adapted to its respective application, with the highest stiffness and strength values are achieved with continuous fibers and / or wire. The embedding of the reinforcing element in the elastomeric sealing body can be carried out, for example, directly in an extruder, depending on the configuration of the reinforcing element.

In a further embodiment of the invention, it is provided that the elastomeric sealant acrylonitrile-butadiene-styrene and / or a polyamide and / or a polylacetate and / or a polyacrylate and / or a polycarbonate and / or a polyethylene terephthalate and / or poly- ethylene and / or polypropylene and / or polystyrene and / or a polyether ketone and / or Polyvinyl chloride and / or a polyphenylene sulfide and / or a polysulfone and / or a polyetherimide and / or polytetrafluoroethene and / or a polyurethane and / or a polyisoprene and / or a silicone. This also allows the mechanical, chemical and thermal properties of the elastomeric sealing body to be matched optimally to the respective intended use of the inlet lining as well as to the properties of the reinforcing element. It can be provided that the elastomeric sealing body consists of a material mixture, a multilayer material or only of a single material. By the inlet lining is partially made of a thermoset, another way to adapt the mechanical and thermal properties of the inlet lining is possible. It can be provided that the reinforcing element is also embedded in a duroplastic region of the inlet lining. Another aspect of the invention relates to a turbomachine, in particular a

An aircraft engine, comprising a housing, on which an inlet lining is arranged, which comprises an elastomeric sealing body for cooperating with a rotor arranged movable relative to the inlet lining within the housing. In this case, an improved gap attitude according to the invention is achieved in that at least one shape-stabilizing reinforcing element is embedded in the elastomeric sealing body. In contrast to the prior art, when the rotor is rubbed against the inlet lining, the reinforcing element prevents unnecessary damage to the elastomeric sealing body, for example by tearing larger elastomer areas, cracking, overhanging beyond the nominal extent or the like. As a result, a reliable shape stabilization of the inlet lining or the elastomeric sealing body is ensured, whereby the improved gap attitude, a more uniform abrasion and a corresponding increase in efficiency of the turbomachine are guaranteed. At the same time, the reinforcing element advantageously increases the service life of the inlet lining. In principle, it may be provided that the housing and / or the inlet lining is formed segmented or are. Instead of a single reinforcing element, two or more reinforcing elements may be provided. In an advantageous embodiment of the invention it is provided that the inlet lining is designed according to one of the preceding exemplary embodiments. The resulting benefits can be found in the corresponding descriptions.

5

Further advantages result from the turbomachine being designed as a compressor, in particular as a high-pressure and / or low-pressure compressor, and / or as a turbine, in particular as a high-pressure and / or low-pressure turbine. In this way, the advantages that can be achieved by the invention can be realized in a particularly variable manner with a wide variety of flow machine types.

Further features of the invention will become apparent from the claims, the exemplary embodiments and with reference to the drawings. The features and combinations of features mentioned above in the description as well as the features and combinations of features mentioned below in the exemplary embodiment can be used not only in the respectively specified combination but also in other combinations or alone, without departing from the scope of the invention. Showing:

1 is a fragmentary schematic representation of a first exemplary embodiment o an inlet lining with a honeycomb-shaped reinforcing element.

2 is a fragmentary schematic representation of a second exemplary embodiment of the inlet lining with a fiber-reinforced composite reinforcing element;

5

3 is a fragmentary schematic representation of a third exemplary embodiment of the inlet lining with a fabric-shaped reinforcing element. and

Fig. 4 is a fragmentary schematic representation of a fourth embodiment o of the inlet lining with a felt-shaped reinforcing element. 1 shows a fragmentary schematic illustration of a first exemplary embodiment of an inlet lining 10, which is arranged in an aircraft engine housing 12 of a compressor of a gas turbine (not shown). The aircraft engine housing 12, which is also referred to as a Shroud, serves as a carrier of the inlet lining 10 and is formed here segmented. The inlet lining 10, which in turn may in principle be segmented or formed circumferentially, has an elastomeric sealing body 14 for cooperation with a rotor of the gas turbine which is arranged so as to be movable relative to the inlet lining 10. To stabilize the shape of the elastomeric sealing body 14, a reinforcing element 16 is embedded in it, which in the present exemplary embodiment is honeycomb-shaped (so-called honeycomb structure). The reinforcing element 16 consists of diamond fibers (eg Nomex®), while the elastomer sealing body 14 is made of a silicone. Aramid fibers and silicone have the common advantage that they are very temperature resistant. In addition, aramid fibers are characterized by very high strength, high impact strength, high elongation at break and good vibration damping, so that they are ideal for engine construction own.

The reinforcing element 16 prevents when rubbing the rotor, that it comes to an abrasion of the elastomeric sealing body 14 beyond the nominal amount. Furthermore, the reinforcing element 16 prevents larger material breaks or cracking occurring in the elastomeric sealing body 14. As a result, on the one hand, due to the shape stabilization of the elastomeric sealing body 14, an optimum gap position with minimum radial gap is ensured and, on the other hand, a considerable extension of the service life of the inlet lining 10 is achieved. The reinforcing element 16 can basically extend over the entire inlet lining 10 or, as shown in FIG. 1, only over a partial area.

Fig. 2, Fig. 3 and Fig. 4 respectively show a detail of basic embodiments of further embodiments of the inlet cover 10 with differently shaped reinforcing elements 16. In the exemplary embodiment shown in Fig. 2, the reinforcing element 16 is formed fiberteppichformig, while in the in Fig. 3 and Fig. 4 Ausfüh- tion examples shown is formed in a web-shaped or felt-shaped. In principle, different configurations of the reinforcing element 16 may also be provided depending on the location. be seen. Alternatively or additionally, the reinforcing element 16 may also be embedded in multiple layers in the elastomeric sealing body 14. The elastomeric sealing body 14 may in turn consist of different elastomers or elastomer mixtures and / or optionally be combined with an additional Duroplastkörper to accomplish an optimized adjustment of its mechanical and thermal properties. In addition to the respective combination of reinforcing element material and elastomeric sealing body material, for example, the fiber angle, the fiber volume fraction, the layer sequence, etc. of the reinforcing element 16 can be varied.

Claims

claims

1. inlet lining (10) for arrangement on a gas turbine component, in particular a 5 aeroengine housing (12) or an aircraft engine housing segment, for a

Gas turbine, wherein the inlet lining (10) comprises an elastomeric sealing body (14) for interacting with a further movable relative to the inlet lining arranged further component, in particular a rotor, the gas turbine, characterized in that in the elastomeric sealing body (14) at least one shape-stabilizing reinforcing kung element ( 16) is embedded.

2. run-in coating (10) according to claim 1, characterized in that the reinforcing element (16) at least partially wabenformig and / or faserteppichfb ^'RMIG and / or tissue-shaped and / or gelegeförrnig and / or multiaxialgelegeförmig5 and / or woven and / or mattenformig and / or felt-shaped.

3. inlet lining (10) according to claim 1 or 2, characterized in that the reinforcing element (16) inorganic reinforcing fibers, in particular basalt fibers and / or boron fibers and / or glass fibers and / or ceramic fibers and / or silica refasernes, and / or metallic reinforcing fibers and / or organic reinforcing fibers, in particular aramid fibers and / or carbon fibers and / or polyester fibers and / or nylon fibers and / or polyethylene fibers and / or polyacrylamide fibers. 5

4. inlet lining (10) according to one of claims 1 to 3, characterized in that the reinforcing element (16) comprises flattened reinforcing fibers.

5. inlet lining (10) according to one of claims 1 to 4, characterized in that the reinforcing element (16) short fibers and / or long fibers and / or Endlosfa- fibers and / or comprises a wire.

6. inlet lining (10) according to one of claims 1 to 5, characterized in that the elastomeric sealing body (14) Acryhύtril-butadiene-styrene and / or a polyamide and / or a polylacetate and / or a polyacrylate and / or a polycarbonate and / or a polyethylene terephthalate and / or polyethylene and / or polypropylene and / or polystyrene and / or a polyether ketone and / or polyvinyl chloride and / or a polyphenylene sulfide and / or a polysulfone and / or a polyetherimide and / or polytetrafluoroethene and / or a polyurethane and / or a polyisoprene and / or a silicone.

7. inlet lining (10) according to one of claims 1 to 6, characterized in that this partially consists of a thermoset.

8. turbomachine, in particular aircraft engine, with a housing (12) on which an inlet lining (10) is arranged, which comprises an elastomeric sealing body (14) for cooperation with a relatively movable to the inlet lining within the housing (12) arranged rotor, characterized in that at least one shape-stabilizing reinforcing element (16) is embedded in the elastomeric sealing body (14).

9. Turbomachine according to claim 8, characterized in that the inlet lining (10) is designed according to one of claims 1 to 7.

10. Turbomachine according to claim 8 or 9, characterized in that it is designed as a compressor, in particular as high-pressure and / or low-pressure compressor, and / or as a turbine, in particular as high-pressure and / or low-pressure turbine.