# US 7,607,885 B2 · Methods and apparatus for operating gas turbine engines > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 7,607,885 B2 - Document ID: US7607885B2 - Status: Granted - Kind: B2 - Application number: 11/461,042 - Filed: 2006-07-31 - Published: 2009-08-13 - Granted: 2009-10-27 - Earliest claimed: 2006-07-31 - Assignees: General Electric Company - Inventors: Blaine Charles Bosley; Sean Robert Keith; Jeffrey Allen Kress; Richard W. Albrecht, Jr. - Web page: https://patentgrep.com/patent/US7607885B2 ## CPC - F01D 11/08: for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) - F01D 25/14: Casings modified therefor (double casings F01D25/26) - F01D 25/24: Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) - F01D 25/246: {Fastening of diaphragms or stator-rings} - F05D 2260/201: by impingement of a fluid - 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) - 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 A method of operating a gas turbine engine is provided. The method includes channeling cooling air towards a shroud hanger assembly such that the cooling air flows through a cavity defined in the shroud hanger assembly, directing the cooling air through a plurality of cooling passages extending from the cavity, and discharging the air from the plurality of cooling passages towards an impingement baffle to facilitate cooling a shroud hanging from the shroud hanger. ## Claims ### Claim 1 A method of operating a gas turbine engine, said method comprising: channeling cooling air towards a shroud hanger assembly such that the cooling air flows through a screen coupled to a cavity defined in an upstream face of the shroud hanger assembly; directing air into the cavity through the screen; directing the cooling air through a plurality of cooling passages extending from the upstream face of the shroud hanger assembly; and discharging the air from the plurality of cooling passages towards an impingement baffle to facilitate cooling a shroud hanging from the shroud hanger. ### Claim 2 (depends on 1) A method in accordance with claim 1 wherein directing air into the cavity through the screen further comprises: preventing debris from entering the cavity using the screen. ### Claim 3 (depends on 2) A method in accordance with claim 2 further comprising removing the screen for replacement. ### Claim 4 (depends on 2) A method in accordance with claim 2 further comprising: forming a plurality of openings within the screen; and directing air through the screen openings to facilitate cooling the shroud hanger assembly. ### Claim 5 (depends on 4) A method in accordance with claim 4 further comprising: forming a plurality of pockets within the screen; and positioning the screen to prevent debris from entering the plurality of cooling passages. ### Claim 6 A shroud hanger assembly comprising: a shroud hanger; and an impingement baffle that is coupled to said shroud hanger, said shroud hanger comprises a cavity, a plurality of cooling passages defined therein and a screen coupled to an upstream face of said shroud hanger, each said cooling passage extends from the upstream face of said shroud hanger through said shroud hanger for channeling cooling air towards said impingement baffle, at least two of said cooling passages are coupled together in flow communication via said cavity. ### Claim 7 (depends on 6) A shroud hanger assembly in accordance with claim 6 wherein said cavity is coupled in flow communication with each of said plurality of cooling passages. ### Claim 8 (depends on 6) A shroud hanger assembly in accordance with claim 6 wherein said impingement baffle comprising orifices extending therethrough facilitates impingement cooling of a shroud radially inward from said shroud hanger assembly wherein cooling air flows through said orifices. ### Claim 9 (depends on 6) A shroud hanger assembly in accordance with claim 6 wherein said screen facilitates preventing debris from restricting air flow to said plurality of cooling passages. ### Claim 10 (depends on 6) A shroud hanger assembly in accordance with claim 6 wherein said screen comprises a plurality of openings extending therethrough and at least one recessed pocket. ### Claim 11 (depends on 6) A shroud hanger assembly in accordance with claim 6 wherein said screen comprises a plurality of openings extending therethrough and at least one convex pocket. ### Claim 12 A gas turbine engine comprising: a compressor; and a turbine assembly coupled downstream said compressor, said turbine assembly comprising a shroud hanger assembly at least partially circumscribing the engine, said shroud hanger assembly comprising: a shroud hanger; and an impingement baffle that is coupled to said shroud hanger, said shroud hanger comprises a cavity, a plurality of cooling passages defined therein and a screen coupled to an upstream face of said shroud hanger, each said cooling passage extends from the upstream face of said shroud hanger through said shroud hanger for channeling cooling air towards said impingement baffle, at least two of said cooling passages are coupled together in flow communication via said cavity. ### Claim 13 (depends on 12) A gas turbine engine in accordance with claim 12 wherein said cavity is coupled in flow communication with each of said plurality of cooling passages. ### Claim 14 (depends on 12) A gas turbine engine in accordance with claim 12 wherein said impingement baffle comprising orifices extending therethrough facilitates impingement cooling of a shroud radially inward from said shroud hanger assembly wherein cooling air flows through said orifices. ### Claim 15 (depends on 12) A gas turbine engine in accordance with claim 12 wherein said screen comprises a plurality of openings extending therethrough and at least one recessed pocket. ### Claim 16 (depends on 12) A gas turbine engine in accordance with claim 12 wherein said screen comprises a plurality of openings extending therethrough and at least one convex pocket. ### Claim 17 (depends on 12) A gas turbine engine in accordance with claim 12 wherein said screen facilitates preventing debris from restricting air flow to said plurality of cooling passages.