Patent Application
20140255170
The present invention relates to a component of a gas turbine engine, the component being formed from a continuous fibre reinforced ceramic matrix composite (CMC),
The performance of gas turbine engines, whether measured in terms of efficiency or specific output, is improved by increasing the turbine gas temperature. It is therefore desirable to operate the turbines at the highest possible temperatures. For any engine cycle compression ratio or bypass ratio, increasing the turbine entry gas temperature produces more specific thrust (e.g. engine thrust per unit of air mass flow). However, as turbine entry temperatures increase, it is necessary to develop components and materials better able to withstand the increased temperatures.
This has led to the replacement of metallic components, such as shroud segments, with CMC components having higher temperature capabilities. To accommodate the change in material, however, adaptations to the components have been proposed. For example, EP 0751104 discloses a ceramic segment having an abradable seal which is suitable for use with nickel base turbine blades, and EP 1965030 discloses a hollow section ceramic seal segment. For improved strength and toughness, the CMC can be continuous fibre reinforced.
Gas turbine engine components often require sealing, e.g. to retain a back face air pressure, maintain cooling flows and protect specific fuel consumption (SFC). For example.
The strip and bird mouth seals are suitable for use with metallic seal segments. In particular, such seals require the segments to have high tolerance surface finishes of the type that can be achieved with metallic components. However, a problem associated with continuous fibre reinforced CMCs is that they generally have a surface texture similar to a woven fabric, which is not a suitable sealing face. The CMC surface can be ground to a high tolerance, but porosity in the CMC can then reduce sealing efficiency.
It would be desirable to provide a continuous fibre reinforced CMC component having improved sealing capability.
Accordingly, in a first aspect the present invention provides a component of a gas turbine engine, the component being formed from a continuous fibre reinforced CMC;
Advantageously, the filler (whether a finer grade ceramic, metal or intermetallic) can provide the component with a reduced surface roughness and reduced porosity. Further, by providing the filler in the recess it can be embedded in the CMC, whereby the filler, which may be less damage tolerant than the CMC, can be protected on multiple sides by the CMC.
In a second aspect the present invention provides a gas turbine engine fitted with the component of the first aspect.
Optional features of the invention will now be set out. These are applicable singly or in any combination with any aspect of the invention.
Preferably the recess is filled with the finer grade ceramic. This may be a monolithic ceramic. Another option, however, is for the finer grade ceramic to be another CMC, e.g. a short-fibre or particulate reinforced CMC.
The finer grade ceramic may have substantially the same composition as the ceramic matrix of the CMC. In this way the chemical and mechanical compatibility can be improved. For example, the thermal expansion coefficients of the finer grade ceramic and the ceramic matrix of the CMC can be matched.
On the other hand, a metal or intermetallic filler may be adopted Such a filler may provide a more compatible surface for contact with the flexible seal than a ceramic filler can provide. However, the metal or intermetallic would generally need to be relatively thin to prevent excessive stresses and strains in the surrounding CMC. Also the metal or intermetallic should be able to withstand the operating temperature at the sealing portion.
The sealing contact between the component and the adjacent component can be effected by a flexible sealing member which conforms to the surface of the sealing portion. Thus the flexible sealing member can be an alternative to a strip seal or a bird mouth seal. For example, the sealing member can be a convolute seal such as a C-seal, a W-seal, an omega-seal or a bellow seal.
The component can be a seal segment for a shroud ring of a rotor of the engine, the seal segment being positioned, in use, radially adjacent the rotor. The adjacent component may be a casing of rotor. The recess can be a channel formed in a face of the segment, such as a back face distal from the rotor. For example, the channel may extend around the periphery of the face.
Alternatively, the component can be a nozzle guide vane. Such a vane may have an aerofoil body which extends between inner and outer endwall platforms, the recess being formed in one of the platforms. Indeed, a filled recess may be formed in each platform The adjacent component may be a neighbouring endwall component (i.e. to front or rear of the platform, or it may be the platform of a next nozzle guide vane in a row of guide vanes).
Embodiments of the invention will now be described by way of example with reference to the accompanying drawings in which:
With reference to
During operation, air entering the intake 11 is accelerated by the fan 12 to produce two air flows: a first air flow A into the intermediate pressure compressor 13 and a second air flow B which passes through the bypass duct 22 to provide propulsive thrust. The intermediate pressure compressor 13 compresses the air flow A directed into it before delivering that air to the high pressure compressor 14 where further compression takes place.
The compressed air exhausted from the high-pressure compressor 14 is directed into the combustion equipment 15 where it is mixed with fuel and the mixture combusted. The resultant hot combustion products then expand through, and thereby drive the high, intermediate and low-pressure turbines 16, 17, 18 before being exhausted through the nozzle 19 to provide additional propulsive thrust. The high, intermediate and low-pressure turbines respectively drive the high and intermediate pressure compressors 14, 13 and the fan 12 by suitable interconnecting shafts.
The high pressure turbine 16 includes an annular array of radially extending, shroudless rotor aerofoil blades A shroud ring is positioned radially outwardly of the aerofoil blades.
The shroud ring serves to define the radially outer extent of a short length of the gas passage through the high pressure turbine 16.
The turbine gases flowing over the radially inward facing surface of the shroud ring are at extremely high temperatures. Consequently, the shroud ring is formed from an annular row of continuous fibre reinforced CMC seal segments, which are capable of withstanding those temperatures whilst maintaining their structural integrity.
Instead of or in addition to sealing the edges of the segment (e.g. with strip seals and/or bird mouth seals), a flexible convolute seal (such as a C-seal, W-seal, omega-seal or bellow seal) is used on the back face 34 of the segment near to the edges. The seal conforms to the segment back surface, taking on the general shape of the back face. However, because the seal would not conform well to the surface roughness created by the plies of reinforcing fibre, and because a machined CMC surface would have surface porosity that would reduce the effectiveness of a seal, a finer grade ceramic is embedded in the back face to provide a sealing portion of the segment.
More particularly, and as shown in
While the invention has been described in conjunction with the exemplary embodiments described above, many equivalent modifications and variations will be apparent to those skilled in the art when given this disclosure. For example, the continuous fibre reinforced CMC component having a recessed sealing portion formed of finer grade ceramic may be another component of a gas turbine engine, such as nozzle guide vane, and in particular an endwall of such a vane. In another example, the channel may be filled with a metal or an intermetallic rather than finer grade ceramic. A metal or intermetallic would tend to provide a more compatible surface for contact with the flexible seal, and can also be embedded by casting in situ, spraying in situ, or pre-casting and bonding. However, the metal or intermetallic would generally need to be relatively thin to prevent excessive stresses and strains in the surrounding CMC. Also the metal or intermetallic should be able to withstand the operating temperature at the seal location. Accordingly, the exemplary embodiments of the invention set forth above are considered to be illustrative and not limiting. Various changes to the described embodiments may be made without departing from the spirit and scope of the invention.
| Number | Date | Country | Kind |
|---|---|---|---|
| 1303995.3 | Mar 2013 | GB | national |
