# US 12,180,911 B2 · Ducted firewall with upper bifi bleed for modulated core ventilation > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,180,911 B2 - Document ID: US12180911B2 - Status: Granted - Kind: B2 - Application number: 18/137,887 - Filed: 2023-04-21 - Published: 2024-10-24 - Granted: 2024-12-31 - Earliest claimed: 2023-04-21 - Assignees: Rtx Corporation - Applicants: Raytheon Technologies Corporation - Inventors: Murat Yazici; Marc J. Muldoon - Web page: https://patentgrep.com/patent/US12180911B2 ## CPC - F02C 6/08: the gas being bled from the gas-turbine compressor - F02K 3/04: the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type - 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 17/148: {by means of rotatable members, e.g. butterfly valves} - F01D 25/14: Casings modified therefor (double casings F01D25/26) - F02C 6/06: providing compressed gas (F02C6/10 takes precedence) - F02C 7/18: the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} - F02C 7/25: Fire protection or prevention (in general A62) - F04D 27/009: {by bleeding, by passing or recycling fluid} - B64D 2045/009: {Fire detection or protection; Erosion protection, e.g. from airborne particles} - F05D 2240/121: related to the leading edge of a stator vane - F05D 2260/608: Aeration, ventilation, dehumidification or moisture removal of closed spaces - 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) - 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) - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F04D: NON-POSITIVE-DISPLACEMENT PUMPS (engine fuel-injection pumps F02M; ion pumps H01J41/12; electrodynamic pumps H02K44/02) - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract A gas turbine engine is provided that includes fan, compressor, combustor, and turbine sections, an outer casing, an outside core annular region, and a fan air circulation system. The outer casing is disposed radially outside of the compressor, combustor, and turbine sections. The engine has a core gas path and a fan bypass air duct. The core gas path extends through the compressor, combustor, and turbine sections, and is disposed radially inside of the outer casing. The fan bypass air duct is defined by inner and outer radial flow path boundaries. The outside core annular region is disposed radially between the outer casing and the inner radial boundary flow path boundary. The fan air circulation system is configured to receive fan bypass air from the fan bypass air duct and selectively pass the received fan bypass air into the outside core annular region. ## Claims ### Claim 1 A gas turbine engine, comprising: a fan section; a compressor section; a combustor section; a turbine section; an outer casing disposed radially outside of the compressor section, combustor section, and the turbine section; wherein the engine has a core gas path that extends through the compressor section, the combustor section, and the turbine section, the core gas path disposed radially inside of the outer casing, and a fan bypass air duct defined by an inner radial flow path boundary and an outer radial flow path boundary, and a member disposed within the fan bypass air duct and extending between the inner radial flow path boundary and the outer radial flow path boundary; an outside core annular region radially disposed between the outer casing and the inner radial flow path boundary; an aft fan annular compartment disposed forward of the outside core annular region and defined by the outer casing, an annular aft inner diameter panel and a firewall; and a fan air circulation system that includes an air inlet disposed within the member and a manifold disposed within the aft fan annular compartment, wherein the fan air circulation system is configured to selectively pass a flow of fan bypass air received from the fan bypass air duct through the air inlet and into the manifold, and pass the flow of fan bypass air into the outside core annular region from the manifold. ### Claim 2 (depends on 1) The gas turbine engine of claim 1, wherein the fan air circulation system includes a valve that is disposable in a closed configuration and an open configuration, wherein in the open configuration, the flow of fan bypass air into the outside core annular region is volumetrically greater than the flow of fan bypass air into the outside core annular region in the closed configuration. ### Claim 3 (depends on 2) The gas turbine engine of claim 2, wherein the valve can be controlled to move from the closed configuration to the open configuration, and can be controlled to move from the open configuration to the closed configuration. ### Claim 4 (depends on 3) The gas turbine engine of claim 3, wherein the valve can be controlled to move to a plurality of open configurations. ### Claim 5 (depends on 4) The gas turbine engine of claim 4, wherein the plurality of open configurations include a fully open configuration and one or more partially open configurations, and wherein the flow of fan bypass air into the outside core annular region in a said partially open configuration is volumetrically less than the flow of fan bypass air into the outside core annular region in the fully open configuration. ### Claim 6 (depends on 1) The gas turbine engine of claim 1, wherein the fan air circulation system further includes a plurality of exit ports in communication with the manifold, wherein the plurality of exit ports are disposed such that the flow of fan bypass air passes through the plurality of exit ports between the manifold and the outside core annular region. ### Claim 7 (depends on 6) The gas turbine engine of claim 6, wherein the exit ports are spaced apart from one another circumferentially. ### Claim 8 (depends on 7) The gas turbine engine of claim 7 wherein the manifold extends circumferentially and the exit ports are spaced equidistant from one another around a circumference of the manifold. ### Claim 9 (depends on 7) The gas turbine engine of claim 7 wherein the manifold extends circumferentially and the exit ports are non-uniformly spaced from one another around a circumference of the manifold. ### Claim 10 (depends on 7) The gas turbine engine of claim 7, wherein each of the exit ports has the same fluid flow characteristics. ### Claim 11 (depends on 7) The gas turbine engine of claim 7, wherein the plurality of exit ports includes a first exit port having a first fluid flow characteristic and a second exit port having a second fluid flow characteristic, and the first fluid flow characteristic is different from the second fluid flow characteristic. ### Claim 12 (depends on 1) The gas turbine engine of claim 1, wherein the fan air circulation system includes a valve that is disposed in the member, which valve is controllable to be disposed in a closed configuration or an open configuration. ### Claim 13 (depends on 12) The gas turbine engine of claim 12, wherein the fan air circulation system includes a plurality of exit ports in communication with the manifold; and wherein the manifold is attached to the firewall and the plurality of exit ports extend through the firewall. ### Claim 14 (depends on 13) The gas turbine engine of claim 13, wherein the firewall separates the aft fan annular compartment from the outside core annular region. ### Claim 15 (depends on 1) The gas turbine engine of claim 1, wherein the air inlet is disposed in the member at a position that is proximate to but spaced apart from an aft inner diameter panel. ### Claim 16 (depends on 15) The gas turbine engine of claim 15, wherein the air inlet is configured to function as a ram air inlet. ### Claim 17 A method of cooling one or more external components of a gas turbine engine, the gas turbine engine including a fan section, a compressor section, a combustor section, a turbine section, and an outer casing disposed radially outside of the compressor section, combustor section, and the turbine section, wherein the gas turbine engine has a core gas path that extends through the compressor section, the combustor section, and the turbine section, the core gas path disposed radially inside of the outer casing, a fan bypass air duct defined by an inner radial flow path boundary and an outer radial flow path boundary, a member extending between the inner radial flow path boundary and the outer radial flow path boundary, the member including an air inlet configured to receive a flow of fan bypass air from the fan bypass air duct, and an outside core annular region radially disposed between the outer casing and the inner radial boundary flow path boundary, an aft fan annular compartment disposed forward of the outside core annular region and defined by the outer casing, an annular aft inner diameter panel, and a firewall, wherein the one or more external components are disposed in the outside core annular region, the method comprising: using a valve to selectively control passage of a flow of fan bypass air from the air inlet disposed within the member to a manifold disposed within the aft fan annular compartment, and thereafter into to the outside core annular region, wherein the valve is controllable to move from a first configuration to a second configuration, and controllable to move from the second configuration to the first configuration, wherein in the second configuration, the flow of fan bypass air into the outside core annular region is volumetrically greater than the flow of fan bypass air into the outside core annular region in the first configuration. ### Claim 18 A gas turbine engine, comprising: a fan section; a compressor section; a combustor section; a turbine section; an outer casing disposed radially outside of the compressor section, combustor section, and the turbine section; wherein the engine has a core gas path that extends through the compressor section, the combustor section, and the turbine section, the core gas path disposed radially inside of the outer casing, a fan bypass air duct defined by an inner radial flow path boundary and an outer radial flow path boundary, and a member extending between the inner radial flow path boundary and the outer radial flow path boundary; an outside core annular region radially disposed between the outer casing and the inner radial boundary flow path boundary; an aft fan annular compartment disposed forward of the outside core annular region, wherein the aft fan annular compartment is defined by the outer casing, an annular aft inner diameter panel, and a firewall; a fan air circulation system that includes an air inlet disposed within the member,-and-a manifold disposed within the aft fan annular compartment, and a valve, wherein the fan circulation system defines a fan bypass air flow passage that extends from the air inlet, through the manifold, and into the outside core annular region; and a system controller in communication with the valve and a non-transitory memory storing instructions, which instructions when executed cause the system controller to: selectively control passage of the flow of fan bypass air into the outside core annular region using the valve, the selective control including passing a first said flow of fan bypass air into the outside core annular region during a first engine operating condition, and passing a second said flow of fan bypass air into the outside core annular region during a second engine operating condition, wherein the first said flow of fan bypass air is volumetrically greater than the second said flow of fan bypass air. ### Claim 19 (depends on 18) The gas turbine engine of claim 18, wherein the first engine operating condition is a take-off condition and the second engine operating condition is a cruise condition. ### Claim 20 (depends on 18) The gas turbine engine of claim 18, wherein the selectively controlled passage of the flow of fan bypass air into the outside core annular region is based on a thermal environment within the outside core annular region.