# US 10,502,160 B2 · Reverse thrust engine > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,502,160 B2 - Document ID: US10502160B2 - Status: Granted - Kind: B2 - Application number: 15/018,893 - Filed: 2016-02-09 - Published: 2017-08-10 - Granted: 2019-12-10 - Earliest claimed: 2016-02-09 - Assignees: General Electric Company - Applicants: General Electric Company - Inventors: Tsuguji Nakano; Andrew Breeze-Stringfellow - Web page: https://patentgrep.com/patent/US10502160B2 ## CPC - F02K 1/68: Reversers mounted on the engine housing downstream of the fan exhaust section - F01D 1/30: characterised by having a single rotor operable in either direction of rotation, e.g. by reversing of blades (combinations of machines or engines F01D13/00) - F01D 7/00: Rotors with blades adjustable in operation; Control thereof (for reversing F01D1/30) - F02C 9/18: by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)} - F02K 1/64: Reversing fan flow - F02K 1/66: using reversing fan blades - F02K 1/766: {with blocking systems or locking devices; Arrangement of locking devices for thrust reversers} - F02K 3/075: controlling flow ratio between flows - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - 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) - 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) - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A propulsion device that defines a central axis and a circumferential direction is provided. The propulsion device may include a core engine and a core casing. The core engine may include an engine shaft extending along the central axis. The core casing may have an inner surface and an outer surface. The core casing may extend along the circumferential direction about the propulsion device, as well as along the central axis from a forward end to an aft end. The core casing may define a primary air flowpath having an annular inlet at the forward end and an exhaust at the aft end. The core casing may further define a reverse flow passage extending from an outer surface entrance to an inner surface exit. ## Claims ### Claim 1 A propulsion device defining a central axis and a circumferential direction, the propulsion device comprising: a core engine having an engine shaft extending along the central axis; and a core casing having an inner surface and an outer surface, the core casing extending along the circumferential direction about the propulsion device and extending along the central axis from a forward end to an aft end, the core casing defining a primary air flowpath having an annular inlet at the forward end and an exhaust at the aft end, the core casing further defining a reverse flow passage extending from an outer surface entrance to an inner surface exit, wherein the inner surface exit is defined through the inner surface, wherein the inner surface exit is defined aft of a core strut and forward of at least a portion of a low pressure compressor, wherein the outer surface entrance is defined through the outer surface and at least partially through a bypass outlet guide vane. ### Claim 2 (depends on 1) The propulsion device of claim 1, wherein the low pressure compressor is attached to the engine shaft, and wherein the core engine further comprises: a combustion section positioned downstream of the low pressure compressor to receive a compressed fluid from the low pressure compressor, and a turbine attached to the engine shaft and positioned downstream of the combustion section, the turbine configured to provide a rotational force to the compressor through the engine shaft. ### Claim 3 (depends on 1) The propulsion device of claim 1, wherein the reverse flow passage defines an arcuate flowpath through the core casing to direct air into the primary air flowpath at a location forward of the low pressure compressor. ### Claim 4 (depends on 1) The propulsion device of claim 1, wherein the core engine further defines a radial direction, wherein the core strut extends inward from the inner surface of the core casing along the radial direction, the core strut being positioned between the annular inlet and the inner surface exit along the central axis. ### Claim 5 (depends on 4) The propulsion device of claim 4, further comprising: a stator vane extending radially inward from the inner surface of the core casing, the stator vane being positioned between the annular inlet and the core strut along the central axis. ### Claim 6 (depends on 1) The propulsion device of claim 1, wherein the bypass outlet guide vane extends radially outward from the outer surface of the core casing, the bypass outlet guide vane being positioned between the forward end and at least a portion of the low pressure compressor. ### Claim 7 (depends on 1) The propulsion device of claim 1, wherein the core engine further defines a radial direction, wherein the core strut extends inward from the inner surface of the core casing along the radial direction, wherein the bypass outlet guide vane extends outward from the outer surface of the core casing along the radial direction, and wherein the bypass outlet guide vane is aligned with the core strut along the central axis to form a rigid radial support line. ### Claim 8 (depends on 3) The propulsion device of claim 3, further comprising: an active control plate attached to the core casing and positioned within the arcuate flowpath to selectively block air through the reverse flow passage. ### Claim 9 (depends on 3) The propulsion device of claim 3, further comprising: a plurality of reverse flow passages spaced along the circumferential direction. ### Claim 10 (depends on 9) The propulsion device of claim 9, wherein the core casing defines a continuous strip along the core casing between each reverse flow passage, and wherein each reverse flow passage extends from an opening defined within the outer surface to an opening defined within the inner surface. ### Claim 11 An engine defining a central axis, the engine comprising: a fan section including a plurality of variable pitch fan blades for generating a forward thrust and a reverse thrust; a core engine drivingly connected to the fan section; and a core casing enclosing the core engine and at least partially defining a primary air flowpath through the core engine, the core casing extending along the central axis from a forward end to an aft end, the core casing defining an annular inlet to the primary air flowpath at the forward end and a reverse flow passage extending through the core casing to the primary air flowpath to allow a flow of air into the primary air flowpath at a location forward of a low pressure compressor when the variable pitch fan blades generate a reverse thrust, wherein an inner surface exit is defined through an inner surface of the core casing and at least partially through a core strut forward of the low pressure compressor, and wherein the reverse flow passage further comprises: an outer surface entrance defined through an outer surface of the core casing, wherein the outer surface entrance is defined aft of a bypass outlet guide vane and forward of at least a portion of the low pressure compressor. ### Claim 12 (depends on 11) The engine of claim 11, wherein the core engine comprises the low pressure compressor, a combustion section, and a turbine, wherein the compressor, the combustion section, and the turbine are arranged in serial flow order. ### Claim 13 (depends on 11) The engine of claim 11, wherein the engine further defines a circumferential direction, the engine further comprising: a continuous fan casing extending along the circumferential direction about the fan blades and at least a portion of the core casing, wherein the continuous fan casing defines a bypass airflow passage between the continuous fan casing and the core casing. ### Claim 14 (depends on 11) The engine of claim 11, wherein the engine further defines a radial direction, wherein the core strut extends inward from the inner surface of the core casing along the radial direction, the core strut being positioned between the annular inlet and the inner surface exit along the central axis, the engine further comprising: a fan exit stator vane extending inward from the inner surface of the core casing along the radial direction, the fan exit stator vane being positioned aft of the fan blades between the annular inlet and the core strut along the central axis. ### Claim 15 (depends on 11) The engine of claim 11, wherein the engine further defines a radial direction, wherein the core strut extends inward from the inner surface of the core casing along the radial direction, and wherein the bypass outlet guide vane extends outward from the outer surface of the core casing along the radial direction, wherein the bypass outlet guide vane is substantially aligned with the core strut along the central axis to form a rigid radial support line. ### Claim 16 (depends on 11) The engine of claim 11, wherein the reverse flow passage defines an arcuate flowpath through the core casing. ### Claim 17 (depends on 11) The engine of claim 11, further comprising: an active control plate attached to the core casing to selectively block air through the reverse flow passage. ### Claim 18 (depends on 11) The engine of claim 11, wherein the engine further defines a circumferential direction, the engine further comprising: a plurality of reverse flow passages spaced along the circumferential direction. ### Claim 19 (depends on 18) The engine of claim 18, wherein the core casing defines a continuous strip along the core casing between each reverse flow passage. ### Claim 20 A method of operating a propulsion device having a fan section with a plurality of variable pitch fan blades for generating a forward thrust and a reverse thrust, a core engine drivingly connected to the fan section, and a core casing, the method comprising: generating reverse thrust utilizing the fan section such that air flows through a reverse flow passage, wherein the reverse flow passage is defined through the core casing, and wherein the core casing encloses the core engine and at least partially defines a primary air flowpath through the core engine, the core casing extending along a central axis from a forward end to an aft end, the core casing defining an annular inlet to the primary air flowpath at the forward end, wherein the core casing has an inner surface and outer surface; articulating an active control plate with an obstruction so as to remove the obstruction from the reverse flow passage, wherein the reverse flow passage defines an arcuate flowpath through the core casing, wherein the active control plate is positioned within and at least partially aft of the arcuate flowpath; and delivering a portion of reverse airflow through the reverse flow passage defined by the core casing and extending from an outer surface entrance to an inner surface exit, wherein the inner surface exit is defined through the inner surface, wherein the inner surface exit is defined aft of a core strut and forward of a low pressure compressor, and wherein the outer surface entrance is defined through the outer surface, wherein the outer surface entrance is defined aft of a bypass outlet guide vane and forward of at least a portion of the low pressure compressor.