# US 2020/0400073 A1 · High pressure clearance control system for gas turbine engine > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2020/0400073 A1 - Document ID: US20200400073A1 - Status: Published application - Kind: A1 - Application number: 16/448,775 - Filed: 2019-06-21 - Published: 2020-12-24 - Earliest claimed: 2019-06-21 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Enzo DiBenedetto; Philip Robert Rioux - Web page: https://patentgrep.com/patent/US20200400073A1 ## CPC - F02C 7/18: the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} - F01D 11/24: by selectively cooling-heating stator or rotor components - 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}) - F02C 6/08: the gas being bled from the gas-turbine compressor - F02K 3/06: with front fan - F05D 2220/32: in gas turbines - F05D 2220/3218: for an intermediate stage of a compressor - F05D 2260/232: characterized by the cooling medium - F05D 2260/606: Bypassing the fluid - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - 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) - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00) - 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 A high pressure compressor for a gas turbine engine. The high pressure compressor including: a clearance control system, the clearance control system including: a control valve fluidly coupled to a source of bleed air of the high pressure compressor, the control valve configured for movement between a first position and a second position; an insulated pipe fluidly coupled to the control valve; and wherein the control valve redirects a portion of the source of bleed air towards an inner case structure of the high pressure compressor and thereafter to the insulated pipe when it is in the first position and wherein the source of bleed air is not redirected towards the inner case structure of the high pressure compressor and the insulated pipe when the control valve is in the second position. ## Claims ### Claim 1 A high pressure compressor for a gas turbine engine, comprising: a clearance control system, the clearance control system comprising: a control valve fluidly coupled to a source of bleed air of the high pressure compressor, the control valve configured for movement between a first position and a second position; an insulated pipe fluidly coupled to the control valve; and wherein the control valve redirects a portion of the source of bleed air towards an inner case structure of the high pressure compressor and thereafter to the insulated pipe when it is in the first position and wherein the source of bleed air is not redirected towards the inner case structure of the high pressure compressor and the insulated pipe when the control valve is in the second position. ### Claim 2 (depends on 1) The high pressure compressor as in claim 1, wherein the source of bleed air is from a stage 3 of the high pressure compressor. ### Claim 3 (depends on 1) The high pressure compressor as in claim 1, wherein the inner case structure is a stage 6 inner case structure of the high pressure compressor. ### Claim 4 (depends on 1) The high pressure compressor as in claim 1, wherein the control valve is one of a plurality of control valves and the insulated pipe is one of a plurality of insulated pipes each of the plurality of insulated pipes being fluidly coupled to one of the plurality of control valves. ### Claim 5 (depends on 1) The high pressure compressor as in claim 1, wherein the clearance control system comprises only a single control valve and the insulated pipe is one of a plurality of insulated pipes each of the plurality of insulated pipes being fluidly coupled to the single control valve. ### Claim 6 (depends on 1) The high pressure compressor as in claim 1, wherein the source of bleed air is redirected to the control valve without it being mixed with any other source of bleed air. ### Claim 7 (depends on 1) The high pressure compressor as in claim 1, wherein the insulated pipe thermally insulates the redirected portion of the source of bleed air from other sources of bleed air that are at a higher temperature than the redirected portion of the source of bleed air. ### Claim 8 (depends on 1) The high pressure compressor as in claim 1, wherein the control valve mixes the redirected portion of the source of bleed air with a portion of the source of bleed air that has not been redirected to provide a source of mixed bleed air, when it is in the first position. ### Claim 9 A gas turbine engine, comprising: a fan section; a compressor section, the compressor section having a low pressure compressor and a high pressure compressor; a combustor section; a turbine section; and wherein the high pressure compressor includes a clearance control system, the clearance control system comprising: a control valve fluidly coupled to a source of bleed air of the high pressure compressor, the control valve configured for movement between a first position and a second position; an insulated pipe fluidly coupled to the control valve; and wherein the control valve redirects a portion of the source of bleed air towards an inner case structure of the high pressure compressor and thereafter to the insulated pipe when it is in the first position and wherein the source of bleed air is not redirected towards the inner case structure of the high pressure compressor and the insulated pipe when the control valve is in the second position. ### Claim 10 (depends on 9) The gas turbine engine as in claim 9, wherein the source of bleed air is from a stage 3 of the high pressure compressor. ### Claim 11 (depends on 9) The gas turbine engine as in claim 9, wherein the inner case structure is a stage 6 inner case structure of the high pressure compressor. ### Claim 12 (depends on 9) The gas turbine engine as in claim 9, wherein the control valve is one of a plurality of control valves and the insulated pipe is one of a plurality of insulated pipes each of the plurality of insulated pipes being fluidly coupled to one of the plurality of control valves. ### Claim 13 (depends on 12) The gas turbine engine as in claim 12, wherein the clearance control system comprises only a single control valve and the insulated pipe is one of a plurality of insulated pipes each of the plurality of insulated pipes being fluidly coupled to the single control valve. ### Claim 14 (depends on 9) The gas turbine engine as in claim 9, wherein the source of bleed air is redirected to the control valve without it being mixed with any other source of bleed air. ### Claim 15 (depends on 9) The gas turbine engine as in claim 9, wherein the insulated pipe thermally insulates the redirected portion of the source of bleed air from other sources of bleed air that are at a higher temperature than the redirected portion of the source of bleed air. ### Claim 16 (depends on 9) The gas turbine engine as in claim 9, wherein the control valve mixes the redirected portion of the source of bleed air with a portion of the source of bleed air that has not been redirected to provide a source of mixed bleed air, when it is in the first position. ### Claim 17 (depends on 16) The gas turbine engine as in claim 16, wherein the source of mixed bleed air is provided to the turbine section. ### Claim 18 A method of cooling a portion of a high pressure compressor of a gas turbine engine, comprising: fluidly coupling a control valve fluidly of a clearance control system to a source of bleed air of the high pressure compressor, the control valve configured for movement between a first position and a second position; fluidly coupling an insulated pipe to the control valve; and redirecting a portion of the source of bleed air towards an inner case structure of the high pressure compressor and thereafter the insulated pipe when the control valve is in the first position and wherein the source of bleed air is not redirected towards the inner case structure of the high pressure compressor and the insulated pipe when the control valve is in the second position. ### Claim 19 (depends on 18) The method as in claim 18, wherein the source of bleed air is from a stage 3 of the high pressure compressor, and wherein the control valve is one of a plurality of control valves and the insulated pipe is one of a plurality of insulated pipes each of the plurality of insulated pipes being fluidly coupled to one of the plurality of control valves. ### Claim 20 (depends on 18) The method as in claim 18, wherein the inner case structure is a stage 6 inner case structure of the high pressure compressor, and wherein the clearance control system comprises only a single control valve and the insulated pipe is one of a plurality of insulated pipes each of the plurality of insulated pipes being fluidly coupled to the single control valve.