# US 9,038,396 B2 · Cooling apparatus for combustor transition piece > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 9,038,396 B2 - Document ID: US9038396B2 - Status: Granted - Kind: B2 - Application number: 12/099,352 - Filed: 2008-04-08 - Published: 2009-10-08 - Granted: 2015-05-26 - Earliest claimed: 2008-04-08 - Assignees: General Electric Company - Applicants: Ronald James Chila; David Purnell - Inventors: Ronald James Chila; David Purnell - Web page: https://patentgrep.com/patent/US9038396B2 ## CPC - F01D 9/023: {Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings} - F01D 25/12: Cooling - F02C 7/18: the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} - F05D 2230/21: by casting - F05D 2230/232: by welding - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract Disclosed is an apparatus for cooling a transition piece of a combustor includes at least one wrapper disposed at the transition piece located outboard of the transition piece. At least one support boss is located between the at least one wrapper and the transition piece. The at least one support boss, the at least one wrapper, and transition piece define at least one cooling flow channel for directing flow for cooling the transition piece. A method of cooling a transition piece of a combustor includes flowing cooling flow into at least one cooling flow channel located at the transition piece, the at least one cooling flow channel defined by the transition piece, at least one wrapper located at the transition piece and located outboard of the transition piece, and at least one support boss located between the at least one wrapper and the transition piece. The cooling flow is directed via the at least one support boss and flows across an outer surface of the transition piece thereby cooling the transition piece. ## Claims ### Claim 1 An apparatus for cooling a transition piece of a combustor comprising: at least one wrapper disposed at the transition piece located outboard of the transition piece; and at least one support boss disposed between the at least one wrapper and the transition piece, the at least one support boss, the at least one wrapper, and transition piece defining at least one cooling flow channel for directing flow for cooling the transition piece, the at least one support boss redirecting the flow from a substantially axially-directed flow to a substantially circumferentially-directed flow. ### Claim 2 (depends on 1) The apparatus of claim 1 wherein the at least one support boss is at least one airfoil. ### Claim 3 (depends on 1) The apparatus of claim 1 wherein the flow is discharge flow from a compressor. ### Claim 4 (depends on 1) The apparatus of claim 1 wherein the at least one wrapper is formed from a metal. ### Claim 5 (depends on 1) The apparatus of claim 1 wherein the at least one support boss is secured to at least one of the at least one wrapper and the transition piece. ### Claim 6 (depends on 5) The apparatus of claim 5 wherein the at least one support boss is secured to at least one of the at least one wrapper and the transition piece by welding. ### Claim 7 (depends on 1) The apparatus of claim 1 wherein the at least one wrapper includes at least one wrapper hole for providing additional flow into the at least one cooling flow channel. ### Claim 8 (depends on 1) The apparatus of claim 1 wherein the at least one wrapper includes a leading edge having a radius for reducing a pressure drop at an entrance to the at least one cooling flow channel. ### Claim 9 A gas turbine comprising: at least one combustion chamber; at least one turbine; at least one transition piece disposed in flow communication with the at least one combustion chamber and the at least one turbine for conveying combustion gas from the at least one combustion chamber to the at least one turbine; at least one wrapper disposed at the at least one transition piece and located outboard of the at least one transition piece; and at least one support boss disposed between the at least one wrapper and the at least one transition piece, the at least one support boss, the at least one wrapper, and the at least one transition piece defining at least one cooling flow channel for directing cooling flow for cooling the at least one transition piece, the at least one support boss redirecting the flow from a substantially axially-directed flow to a substantially circumferentially-directed flow. ### Claim 10 (depends on 9) The gas turbine of claim 9 wherein the at least one support boss is at least one airfoil. ### Claim 11 (depends on 9) The gas turbine of claim 9 wherein the cooling flow is discharge flow from a compressor. ### Claim 12 (depends on 9) The gas turbine of claim 9 wherein the at least one wrapper is at least partially disposed between adjacent transition pieces of the at least one transition piece. ### Claim 13 (depends on 9) The gas turbine of claim 9 wherein the at least one wrapper is formed from a metal. ### Claim 14 (depends on 9) The gas turbine of claim 9 wherein the at least one support boss is secured to at least one of the at least one wrapper and the at least one transition piece. ### Claim 15 (depends on 14) The gas turbine of claim 14 wherein the at least one support boss is secured to at least one of the at least one wrapper and the at least one transition piece by welding. ### Claim 16 (depends on 9) The gas turbine of claim 9 wherein the at least one wrapper includes at least one wrapper hole for providing additional flow into the at least one cooling flow channel. ### Claim 17 (depends on 9) The gas turbine of claim 9 wherein the at least one wrapper includes a leading edge having a radius for reducing a pressure drop at an entrance to the at least one cooling flow channel. ### Claim 18 A method of cooling a transition piece of a combustor comprising: flowing cooling flow into at least one cooling flow channel disposed at the transition piece, the at least one cooling flow channel defined by the transition piece, at least one wrapper disposed at the transition piece and located outboard of the transition piece, and at least one airfoil disposed between the at least one wrapper and the transition piece; directing the cooling flow from a substantially axially-directed cooling flow to a substantially circumferentially-directed cooling flow via the at least one airfoil; flowing the cooling flow across an outer surface of the transition piece thereby cooling the transition piece. ### Claim 19 (depends on 18) The method of claim 18 including inputting additional cooling flow into the at least one cooling flow channel via at least one wrapper hole disposed in the at least one wrapper. ### Claim 20 (depends on 18) The method of claim 18 wherein the cooling flow is discharge flow from a compressor.