Combustor dome tiles

A tile for a combustor dome of a gas turbine engine includes a tile body defining an upstream surface and an axially opposed downstream surface with at least one injection orifice defined through the tile body from the upstream surface to the downstream surface. The tile body extends in a radial direction from a radially inner surface to a radially outer surface. The radially inner and outer surfaces define circular arcs that are concentric with one another. The tile body extends circumferentially from a first end face to a second end face. The first end face follows a sigmoid profile and the second end face follows a sigmoid profile configured to interlock with the sigmoid profile of the first end face of another identical tile body.

BACKGROUND OF THE INVENTION

1. Field of the Invention

The present disclosure relates to combustion, and more particularly to multipoint injection systems such as used for combustion in gas turbine engines.

2. Description of Related Art

Multipoint fuel injection systems would benefit from simple, low cost fuel injectors, manifolds, and dome construction to permit a large number of injectors to be used. Traditional fuel injector and nozzle designs require complex manifolding that can impede air flow from a compressor to the combustor in a gas turbine engine. Combustor dome designs and fuel injection systems can be expected to become more integrated with one another as the drive for ever greater engine pressure ratios, fuel efficiency, and reduced emissions continues.

Such conventional methods and systems have generally been considered satisfactory for their intended purpose. However, there is still a need in the art for improved multipoint combustion systems. The present disclosure provides a solution for this need.

SUMMARY OF THE INVENTION

A tile for a combustor dome of a gas turbine engine includes a tile body defining an upstream surface and an axially opposed downstream surface with at least one injection orifice defined through the tile body from the upstream surface to the downstream surface. The tile body extends in a radial direction from a radially inner surface to a radially outer surface. The radially inner and outer surfaces define circular arcs that are concentric with one another. The tile body extends circumferentially from a first end face to a second end face. The first end face follows a sigmoid profile and the second end face follows a sigmoid profile configured to interlock with the sigmoid profile of the first end face of another identical tile body.

The tile body can include a ceramic matrix composite (CMC) material. Each of the first and second end faces of the tile body can define a pair of axially spaced apart channels, wherein each of the channels runs from the radially inner surface to the radially outer surface of the tile body. Each channel of at least one of the pairs of axially spaced apart channels can include a feather seal element seated therein for creating a gas seal between the tile body an identical adjacent tile body. The at least one injection orifice can include six injection orifices, and the first and second end faces can be separated by an angular separation configured so that fifteen identical tile bodies can be circumferentially linked to form a complete annular combustor dome.

A combustor dome includes a plurality of tiles as described above circumferentially linked to form a complete annular combustor dome wall. The first end face of each tile body follows a sigmoid profile and wherein the second end face follows a sigmoid profile interlocked with the sigmoid profile of the first end face of an adjacent tile body.

The plurality of tiles can be sealed end to end with each other against gas flow in an axial direction except through the injection orifices. The sigmoid profiles can radially trap the feather seal elements between each circumferentially adjacent pair of the tile bodies. There can be fifteen identical tile bodies circumferentially linked to form the complete annular combustor dome wall.

A multipoint injection system includes a manifold extending in a circumferential direction defining a plurality of flow passages each having a main portion defined through the manifold in the circumferential direction. A plurality of feed arms extend radially inward from the manifold. Feed arm portions of the flow passages extend through each of the feed arms. A plurality of injection nozzles are included, wherein each of the feed arm portions of the flow passages includes a respective outlet opening with a respective one of the injection nozzles in fluid communication with each of the outlets. A combustor dome as described above is mounted together with the manifold with the injection nozzles extending though the combustor dome. An outer combustor wall is mounted to the manifold. An inner combustor wall is included radially inward from the outer combustor wall, the inner combustor wall mounted to an inner ring supported from radially inward ends of the feed arms. The combustor dome, injection nozzles, inner combustor wall, and outer combustor wall form an enclosure in which a majority of air passing from a compressor side of the combustor dome must pass through the injection nozzles to reach a combustor space defined radially between the inner and outer combustor walls.

The manifold and the inner ring can each include bayonet flanges extending in an axial direction away from the first axial end of the manifold for interlocking the manifold with the combustor dome, the inner combustor wall, and the outer combustor wall.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

Reference will now be made to the drawings wherein like reference numerals identify similar structural features or aspects of the subject disclosure. For purposes of explanation and illustration, and not limitation, a partial view of an exemplary embodiment of a tile for a combustor dome of a gas turbine engine in accordance with the disclosure is shown inFIG. 1and is designated generally by reference character100. Other embodiments of tiles in accordance with the disclosure, or aspects thereof, are provided inFIGS. 2-5, as will be described. The systems and methods described herein can be used to provide sealing against unwanted airflow between a compressor side and a combustor side of a combustor dome, e.g., in a gas turbine engine, and to facilitate assembly of a combustor dome into a combustion system of a gas turbine engine.

InFIG. 1, two tiles100are shown. Each tile100includes a tile body102defining an upstream104surface relative to the axis A, e.g., the upstream surface104is on the compressor side of the tile body102, and an axially opposed downstream surface106, e.g., on the combustor side. The tile body102can include a ceramic matrix composite (CMC) material, however metallic or other suitable materials can be used without departing from the scope of this disclosure. Each tile100has six injection orifices108defined through the tile body102from the upstream surface104to the downstream surface106, however those skilled in the art will readily appreciate that any other suitable number of injection orifices can be used without departing from the scope of this disclosure.

The tile body102extends in a radial direction relative to the axis A from a radially inner surface110to a radially outer surface112. The radially inner and outer surfaces110,112define circular arcs that are concentric with one another, i.e., centered on the axis A. Each tile body102extends circumferentially from a first end face114to a second end face116. The first end face114follows a sigmoid profile and the second end face116follows a sigmoid profile configured to interlock with the sigmoid profile of the first end face114of another identical adjacent tile body102.

Each of the first and second end faces114,116of each tile body102defines a pair of axially spaced apart channels118,120, wherein each of the channels118,120runs from the radially inner surface110to the radially outer surface112of the tile body102. When assembled into a combustor dome124as shown inFIG. 2, each channel118,120includes a feather seal element122seated therein for creating a gas seal between the tile body102an identical, adjacent tile body102. The feather seal elements122can be metallic or ceramic matrix composite material.

The first and second end faces114,116are separated by an angular separation configured so that fifteen identical tile bodies102can be circumferentially linked to form a wall of a complete annular combustor dome124as shown inFIG. 3, wherein the sigmoid profile of first end face114(labeled inFIG. 1) of each tile body102is interlocked with the sigmoid profile of the second end face116(labeled inFIG. 1) of an adjacent tile body102. Those skilled in the art will readily appreciate that any suitable number of tiles can be used to form a combustor dome without departing from the scope of this disclosure. The plurality of tiles102are sealed end to end circumferentially with each other against gas flow in an axial direction, e.g., in the direction of axis A ofFIG. 1, except through the injection orifices108. The sigmoid profiles of the assembled first and second end faces114,116radially trap the feather seal elements122between each circumferentially adjacent pair of the tile bodies102.

The seams126, labeled inFIG. 2, wherein the first and second end faces114,116are assembled together also form stress relievers at regular intervals around the combustor dome124to reduce stress fractures, e.g., from thermally induced stresses of metallic manifold, feed arm, and injector components that are relatively cold being assembled together with hot CMC components, in undesirable places in the combustor dome124, e.g. places where the air seal between the compressor side and the combustor side of the combustor dome124would be broken. The seams126also provide mechanical accommodation to facilitate assembly of the combustor dome124. Using two feather seal elements122at each seam126allows one feather seal element122to stop axial flow through the seam126and the second feather seal element122to stop radial leakage due to the radial thickness of the tiles100.

With reference now toFIG. 4, a multipoint injection system10includes a manifold12extending in a circumferential direction C defining a plurality of flow passages14each having a main portion defined through the manifold in the circumferential direction, as shown inFIG. 5. A plurality of feed arms16extend radially inward from the manifold12. Feed arm portions17of the flow passages14extend through each of the feed arms16. A plurality of injection nozzles18are included, wherein each of the feed arm portions17of the flow passages14includes a respective outlet20opening with a respective one of the injection nozzles18in fluid communication with each of the outlets20. A combustor dome124as described above is mounted together with the manifold12with the injection nozzles18extending though the injection orifices108of the combustor dome124. Each feed arm16supports six injection nozzles18, which pass through the respective six injection orifices108of a single tile100. It is also contemplated that the feed arms16could straddle the seams126between the tiles100, e.g. with three injection nozzles18of a feed arm16passing through one tile100and three injection nozzles18of the same feed arm16passing through a second, adjacent one of the tiles100.

Referring now toFIG. 5, an outer combustor wall22is mounted to the manifold12. An inner combustor wall24is included radially inward from the outer combustor wall12. The inner combustor wall24is mounted to an inner ring26supported from radially inward ends of the feed arms16. The combustor dome124, injection nozzles18, inner combustor wall24, and outer combustor wall22form an enclosure in which a majority of air passing from a compressor side, e.g. the left side as viewed inFIG. 5, of the combustor dome124must pass through the injection nozzles18to reach a combustor space defined radially between the inner and outer combustor walls22,24.

The manifold12and the inner ring26each include bayonet flanges28extending in an axial direction away from the first axial end of the manifold12for interlocking the manifold12with the combustor dome124, the inner combustor wall24, and the outer combustor wall22.

Systems and methods as disclosed herein provide potential advantages over traditional systems and methods as follows. Fuel tubes and segmented tile construction as disclosed herein provide adaptability in the combustor. Feather seals conforming to segmented tile shapes allow adjustment of tile interfaces while sealing potential leakages through a combustor dome. Adjustable tiles allow for integration of cold, metallic fuel system components together with hot ceramic combustor dome components.

The methods and systems of the present disclosure, as described above and shown in the drawings, provide for combustor domes with superior properties relative to traditional systems including improved sealing against unwanted airflow between a compressor side and a combustor side of a combustor dome, e.g., in a gas turbine engine, and facilitated assembly of a combustor dome into a combustion system of a gas turbine engine. While the apparatus and methods of the subject disclosure have been shown and described with reference to preferred embodiments, those skilled in the art will readily appreciate that changes and/or modifications may be made thereto without departing from the scope of the subject disclosure.