# US 12,110,810 B2 · Gas turbine engine bleed air flow control > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,110,810 B2 - Document ID: US12110810B2 - Status: Granted - Kind: B2 - Application number: 18/158,618 - Filed: 2023-01-24 - Published: 2024-05-16 - Granted: 2024-10-08 - Earliest claimed: 2022-11-16 - Assignees: General Electric Company - Applicants: General Electric Company - Inventors: Kudum Shinde; Sesha Subramanian; Yashpal Patel - Web page: https://patentgrep.com/patent/US12110810B2 ## CPC - F01D 9/06: Fluid supply conduits to nozzles or the like - F01D 17/105: {by passing part of the fluid} - F01D 17/145: {by means of valves, e.g. for steam turbines (valves in general F16K)} - F02C 6/08: the gas being bled from the gas-turbine compressor - F02C 9/18: by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)} - F05D 2220/323: for aircraft propulsion, e.g. jet engines - F05D 2240/14: Casings or housings protecting or supporting assemblies within - F05D 2260/232: characterized by the cooling medium - F05D 2260/605: Venting into the ambient atmosphere or the like - F05D 2260/606: Bypassing the fluid - 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 ## Abstract A gas turbine engine includes a compressor with an inner casing and an outer casing. The inner casing defines a primary flow path for airflow through the compressor, the inner casing and the outer casing define a bleed air cavity therebetween. The inner casing at least partially defines a first bleed air channel between the primary flow path and the first bleed air cavity. The first bleed air channel is defined between a first wall and a second wall, wherein the first wall is upstream from the second wall. The first wall includes a plurality of holes in fluid communication with the primary flow path and fluidly coupled to a suction manifold. The plurality of holes is configured to energize a fluid boundary layer along the first wall. ## Claims ### Claim 1 A gas turbine engine, comprising: a compressor including an inner casing and an outer casing, the inner casing defining a primary flow path for airflow through the compressor, the inner casing and the outer casing defining a first bleed air cavity and a second bleed air cavity therebetween, the inner casing at least partially defining a first bleed air channel between the primary flow path and the first bleed air cavity, wherein the first bleed air channel is defined between a first wall and a second wall, the first wall being upstream from the second wall, wherein the first wall includes a plurality of holes in fluid communication with the primary flow path and fluidly coupled to a suction manifold, wherein the suction manifold is disposed within the first bleed air cavity and is fluidly coupled to the second bleed air cavity, and wherein the plurality of holes is configured to energize a fluid boundary layer along the first wall; and a valve disposed within the first bleed air cavity, wherein the valve is configured to control a flowrate of a portion of the airflow from the primary flow path, through the plurality of holes, into the suction manifold, and into the second bleed air cavity. ### Claim 2 (depends on 1) The gas turbine engine of claim 1, wherein the plurality of holes is angled relative to a radial direction of the gas turbine engine. ### Claim 3 (depends on 1) The gas turbine engine of claim 1, wherein the plurality of holes includes a first row of holes and a second row of holes, wherein the first row of holes is axially spaced from the second row of holes with respect to an axial centerline of the gas turbine engine. ### Claim 4 (depends on 1) The gas turbine engine of claim 1, wherein the compressor further includes a second bleed air channel in fluid communication with the second bleed air cavity and in fluid communication with the primary flow path. ### Claim 5 (depends on 4) The gas turbine engine of claim 4, wherein the second bleed air cavity is pressurized at a lower pressure than the first bleed air cavity. ### Claim 6 (depends on 4) The gas turbine engine as in claim 4, wherein the first bleed air channel of the first bleed air cavity is disposed downstream from the second bleed air channel with respect to the airflow through the compressor. ### Claim 7 (depends on 1) The gas turbine engine of claim 1, wherein the suction manifold extends circumferentially about an outer surface of the inner casing. ### Claim 8 (depends on 1) The gas turbine engine of claim 1, wherein the suction manifold is fluidly coupled to an outer manifold via one or more pipes. ### Claim 9 (depends on 1) The gas turbine engine of claim 1, wherein the compressor includes a low-pressure compressor and a high-pressure compressor in serial flow order, wherein the first bleed air channel and the first bleed air cavity are defined within the high-pressure compressor. ### Claim 10 An aircraft, comprising: a fuselage; a wing attached to the fuselage; and a gas turbine engine, the gas turbine engine comprising: a compressor including an inner casing and an outer casing, the inner casing defining a primary flow path for airflow through the compressor, the inner casing and the outer casing defining a first bleed air cavity and a second bleed air cavity therebetween, the inner casing at least partially defining a first bleed air channel between the primary flow path and the first bleed air cavity to direct a portion of the airflow from the primary flow path into the first bleed air cavity, wherein the first bleed air channel is defined between a first wall and a second wall, the first wall being upstream from the second wall, wherein the first wall includes a plurality of holes in fluid communication with the primary flow path and fluidly coupled to a suction manifold, wherein the suction manifold is disposed within the first bleed air cavity and is fluidly coupled to the second bleed air cavity, and wherein the plurality of holes is configured to energize a fluid boundary layer along the first wall; and a valve disposed within the first bleed air cavity, wherein the valve is configured to control a flowrate of a portion of the airflow from the primary flow path, through the plurality of holes, into the suction manifold, and into the second bleed air cavity. ### Claim 11 (depends on 10) The aircraft of claim 10, wherein the plurality of holes is angled relative to a radial direction of the gas turbine engine. ### Claim 12 (depends on 10) The aircraft of claim 10, wherein the plurality of holes includes a first row of holes and a second row of holes, wherein the first row of holes is axially spaced from the second row of holes with respect to an axial centerline of the gas turbine engine. ### Claim 13 (depends on 10) The aircraft of claim 10, wherein the compressor further includes a second bleed air channel in fluid communication with the second bleed air cavity and in fluid communication with the primary flow path. ### Claim 14 (depends on 13) The aircraft of claim 13, wherein the second bleed air cavity is pressurized at a lower pressure than the first bleed air cavity. ### Claim 15 (depends on 13) The aircraft of claim 13, wherein the first bleed air channel of the first bleed air cavity is disposed downstream from the second bleed air channel with respect to the airflow through the compressor. ### Claim 16 (depends on 11) The aircraft of claim 11, wherein the suction manifold extends circumferentially about an outer surface of the inner casing. ### Claim 17 (depends on 10) The aircraft of claim 10, wherein the suction manifold is fluidly coupled to an outer manifold via one or more pipes. ### Claim 18 (depends on 10) The aircraft of claim 10, wherein the compressor includes a low-pressure compressor and a high-pressure compressor in serial flow order, wherein the first bleed air channel and the first bleed air cavity are defined within the high-pressure compressor.