# US 6,719,524 B2 · Method of forming a thermally isolated gas turbine engine housing > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 6,719,524 B2 - Document ID: US6719524B2 - Status: Granted - Kind: B2 - Application number: 10/084,858 - Filed: 2002-02-25 - Published: 2003-08-28 - Granted: 2004-04-13 - Earliest claimed: 2002-02-25 - Assignees: Honeywell International Inc. - Inventors: Ly D. Nguyen; Louis Cruse; Ivar Gene Fowkes; Silvestre Salas; William North; Vadanth Kadambi - Web page: https://patentgrep.com/patent/US6719524B2 ## CPC - F01D 9/065: {Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26)} - F01D 25/14: Casings modified therefor (double casings F01D25/26) - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) ## Abstract A method for forming a thermally isolating gas turbine housing from the significantly high temperatures associated with the combustion gases flowing through the housing. A floating liner is positioned within the turbine housing with an outer baffle arranged about the floating liner and an inner baffle arranged within the floating liner. The inner and outer baffles are welled or brazed to the floating liner assembly to form a unitary assembly creating a single, continuous cooling passageway within the housing for collecting heat from adjacent the surfaces of the floating liner and expelling the heat into the combustion exhaust stream. ## Claims ### Claim 1 A method of thermally isolating a turbine engine housing from high temperatures created by combustion gases flowing through the engine housing, comprising the steps of: forming a floating liner assembly with a plurality of openings extending there through; forming an outer baffle assembly with a plurality of openings extending there through; forming an inner baffle assembly with a plurality of openings extending there through; arranging the floating liner assembly, the outer baffle assembly and the inner baffle assembly in the turbine engine housing to form a single passageway for conveying a stream of compressed, cooling air against surfaces of the floating liner to collect heat from the floating liner and expel the heat into the stream of combustion gases flowing through turbine engine housing; and forming the housing with an outer ring-shaped housing member and an inner hub connected by a number of hollow housing struts having lengthwise passages for delivering air/oil from the outer ring-shaped housing member to the inner hub. ### Claim 2 (depends on 1) The method according to claim 1, including the step of forming the floating liner assembly as a single member having a generally cylindrically-shaped configuration including outer and inner ring portions separated by a plurality of hollow liner struts. ### Claim 3 (depends on 1) The method according to claim 1, including the step of forming the floating liner assembly as separate inner and outer ring-shaped liner members each having a number of openings, and forming a plurality of hollow struts extending between the ring-shaped liner members forming a cooling air passageway adjacent each of the floating liner ring-shaped members. ### Claim 4 (depends on 3) The method according to claim 3, including the step of welding inner ring-shaped liner member within the outer ring-shaped liner member to form the floating liner assembly. ### Claim 5 (depends on 4) The method according to claim 4, including the step of positioning the outer baffle assembly about the outer ring-shaped liner member before arranging the inner ring-shaped liner member within the outer ring-shaped liner member. ### Claim 6 (depends on 4) The method according to claim 4, including the step of positioning the inner baffle assembly within the inner ring-shaped liner member before arranging the inner ring-shaped liner member within the outer ring-shaped liner member. ### Claim 7 (depends on 1) The method according to claim 1, including the step of forming the outer baffle assembly from two separate baffle members each having a generally cylindrically-shaped configuration and a number of through openings forming cooling air passageways. ### Claim 8 (depends on 7) The method according to claim 7, including the step of welding the two separate outer baffle members to form a single, generally cylindrically-shaped member. ### Claim 9 (depends on 1) The method according to claim 1, including the step of forming the outer baffle assembly as a single, generally cylindrically-shaped member having a plurality of through openings forming cooling air passageways extending there through. ### Claim 10 (depends on 1) The method according to claim 1, including the step of forming the inner baffle assembly from a pair of similarly-shaped cylindrical members attached to one another and having a number of through openings creating cooling air passageways. ### Claim 11 (depends on 10) The method according to claim 10, including the step of forming each cylindrical inner baffle member from a number of arc-shaped segments attached end-to-end. ### Claim 12 A method for thermally isolating a gas turbine engine housing having an outer ring-shaped housing member and an inner hub attached by housing struts from high temperatures created by combustion gases flowing through the turbine engine, comprising the steps of: positioning a floating liner assembly between the inner hub and the outer ring-shaped housing member and arranging a plurality of liner struts to enclose the housing struts, with a plurality of openings extending through the floating liner; positioning an outer baffle assembly about the floating liner assembly, with a plurality of openings extending through portions of the outer baffle assembly; positioning an inner baffle assembly within the floating liner assembly, with a plurality of openings extending through portions of the inner baffle; creating a single, continuous passageway for delivering pressurized air through openings in the outer ring-shaped housing member that impacts and flows through the openings in the outer baffle assembly, the floating liner assembly, the liner struts and the inner baffle assembly for collecting heat from the floating liner and expelling the heat to a stream of combustion gases flowing through the gas turbine engine; and forming the floating liner assembly as separate inner and outer ring-shaped liner members having a number of openings, forming a cooling air passageway adjacent each of the floating liner ring-shaped members; and welding the inner ring-shaped liner member within the outer ring-shaped liner member to form a unitary floating liner assembly. ### Claim 13 (depends on 12) The method according to claim 12, including the step of forming the outer baffle assembly from two separate baffle members each having a generally cylindrically-shaped configuration and a number of through openings forming cooling air passageways. ### Claim 14 (depends on 13) The method according to claim 13, including the step of welding the two separate outer baffle members to form a single, generally cylindrically-shaped member. ### Claim 15 (depends on 12) The method according to claim 12, including the step of forming the inner baffle assembly from a pair of similarly-shaped cylindrical members attached to one another and having a number of through openings creating cooling air passageways. ### Claim 16 (depends on 15) The method according to claim 15, including the step of forming each cylindrical inner baffle member from a number of arc-shaped segments attached end-to-end. ### Claim 17 (depends on 12) The method according to claim 12, including the step of positioning the outer baffle assembly about the outer ring-shaped floating liner member and positioning the inner baffle assembly within the inner ring-shaped floating liner assembly before positioning the floating liner members with the ring-shaped outer housing member. ### Claim 18 (depends on 17) The method according to claim 17, including the step of brazing the outer baffle assembly, the floating liner members and the inner baffle assembly into a unitary member forming a single air flow through passage extending from the outer housing to a stream of combustion gases flowing through the gas turbine engine. ### Claim 19 A method for thermally isolating a gas turbine outer ring-shaped housing member from high temperatures created by combustion gases flowing through the turbine engine, comprising the steps of: positioning a floating liner assembly between an inner hub and the outer ring-shaped housing member and forming the floating liner assembly from separate, inner and outer ring-shaped liner members, having a number of openings, forming an cooling air passageway around each of the floating liner members; positioning an outer baffle assembly having two similar, generally cylindrically-shaped members to surround the floating liner outer ring-shaped member, and forming the outer baffle assembly with a plurality of through openings; positioning an inner baffle assembly having two similar, generally cylindrically-shaped members within the floating liner inner ring-shaped member, and forming the inner baffle assembly with a plurality of through openings; and creating a single, continuous passageway for delivering pressurized air through openings in the outer ring-shaped housing member that impacts and flows through the openings in the outer baffle assembly, the floating liner assembly, the liner struts and the inner baffle assembly for collecting heat from the floating liner and expelling the heat to a stream of combustion gases flowing through the gas turbine engine. ### Claim 20 (depends on 19) The method according to claim 19, including the step of brazing the outer baffle assembly, the floating liner members and the inner baffle assembly into a unitary member forming the single air flow passageway extending from the outer housing to the stream of combustion gases flowing through the gas turbine engine.