초록 ▼

A turbomachine includes a plurality of injection nozzles arranged in a can-annular array and a transition piece including at least one wall that defines a combustion flow passage. A dilution orifice is formed in the at least one wall of the transition piece. The dilution orifice guides dilution gase

A turbomachine includes a plurality of injection nozzles arranged in a can-annular array and a transition piece including at least one wall that defines a combustion flow passage. A dilution orifice is formed in the at least one wall of the transition piece. The dilution orifice guides dilution gases to the combustion flow passage. A heat shield member is mounted to the at least one wall of the transition piece in the combustion flow passage. The heat shield member includes a body having a first surface and an opposing second surface through which extends a dilution passage. The dilution passage is off-set from the dilution orifice. The heat shield member is spaced from the at least one wall of the transition piece defining a flow region between the at least one wall and the second surface.

대표청구항 ▼

1. A turbomachine comprising: a combustor assembly including a combustor liner bounding a flow of combustion gases and having a plurality of injection nozzles arranged in a can-annular array; a transition piece including at least one wall defining a combustion flow passage and bounding the flow of c

1. A turbomachine comprising: a combustor assembly including a combustor liner bounding a flow of combustion gases and having a plurality of injection nozzles arranged in a can-annular array; a transition piece including at least one wall defining a combustion flow passage and bounding the flow of combustion gases;at least one dilution orifice formed in the at least one wall of the transition piece, the at least one dilution orifice guiding dilution gases to the combustion flow passage;a heat shield member mounted to the at least one wall of the transition piece in the combustion flow passage and positioned radially inside of the combustor liner such that a leading edge of the heat shield member is in contact with the flow of combustion gases, the heat shield member including a body having a first surface and an opposing second surface through which extends at least one dilution passage, the at least one dilution passage being off-set from the at least one dilution orifice, the heat shield member being spaced from the at least one wall of the transition piece so as to define a flow region between the at least one wall and the second surface, the flow region thermally decoupling the transition piece from combustion gases produced by the can-annular array of injection nozzles; andat least one mounting member provided on the transition piece; andat least one mounting element provided in the second surface of the heat shield member, the at least one mounting member being adapted to interact with the at least one mounting element to detachably mount the heat shield member to the transition piece. 2. The turbomachine according to claim 1, wherein, the at least one mounting member comprises a hook member extending outward from the at least one wall of the transition piece towards the combustion flow passage, and the at least one mounting element comprises a hook element extending substantially perpendicularly outward from the second surface of the heat shield member, the hook element being configured to couple with the at least one hook member to mount the heat shield member to the at least one wall of the transition piece. 3. The turbomachine according to claim 1, wherein the at least one mounting member comprises an opening that extends through the at least one wall of the transition piece and the at least one mounting element comprises a projection having a first end portion that extends from the second surface towards a second end portion, the second end portion being adapted to extend through the opening to mount the heat shield member to the transition piece. 4. The turbomachine according to claim 3, further comprising: a fastening element provided on the second end portion of the projection. 5. The turbomachine according to claim 4, wherein the second end portion of the projection includes a threaded section. 6. The turbomachine according to claim 4, wherein the fastening element comprises a nut having a plurality of internal threads that are configured to engage with the threaded section of the projection. 7. The turbomachine according to claim 1, wherein the dilution passage includes a first end section that extends to a second end section, the first end section being off-set from the second end section. 8. The turbomachine according to claim 1, wherein the at least one dilution orifice includes a plurality of dilution orifices and the at least one dilution passage includes a plurality of dilution passages, each of the plurality of dilution passages being off-set from each of the plurality of dilution orifices. 9. The turbomachine according to claim 1, wherein the second surface of the heat shield member includes a plurality of protuberances, the plurality of protuberances conditioning an airflow passing through the flow region. 10. A method of thermally decoupling a transition piece from combustion gases in a turbomachine, the method comprising: creating cooling gases in a compressor portion of the turbomachine;generating combustion gases in a plurality of combustion chambers arranged in a can-annular array, each of the plurality of combustion chambers including a combustor liner bounding the flow of combustion gases; guiding the combustion gases into the transition piece of the turbomachine, the transition piece bounding the flow of combustion gases and fluidly connecting the can-annular array of combustion chambers with a first stage of a turbine;shielding an internal surface of the transition piece from the combustion gases with at least one heat shield member, the at least one heat shield member being detachably mounted to and spaced from the internal surface of the transition piece to form a flow cavity, the heat shield positioned radially inside of the combustor liner such that a leading edge of the heat shield member is in contact with the flow of combustion gases;passing the cooling airflow through at least one dilution orifice formed in the transition piece, the dilution orifice being fluidly connected to the flow cavity; andguiding the cooling airflow through at least one dilution passage formed in the at least one heat shield member, the at least one dilution passage being off-set from the at least one dilution orifice so as create an effusion airflow that passes over a surface of the at least one heat shield member to thermally decouple the inner wall of the transition piece from the combustion gases. 11. The method of claim 10, wherein guiding the cooling airflow through the at least one dilution passage comprises passing the cooling airflow into a first end section formed in a first surface of the heat shield member to a second end section, the second end section being off-set from the first end section. 12. The method of claim 10, further comprising: guiding the cooling airflow across a plurality of protuberances formed on the heat shield member. 13. The method of claim 10, wherein, passing the cooling airflow through at least one dilution orifice formed in the transition piece comprises passing the cooling airflow though a plurality of dilution orifices formed in the transition piece. 14. The method of claim 13, wherein, guiding the cooling airflow through at least one dilution passage formed in the at least one heat shield member comprises passing the cooling airflow through a plurality of dilution passages formed in the heat shield member, each of the plurality of dilution passages being off-set from respective ones of the plurality of dilution orifices.