# US 12,110,828 B2 · Gas turbine engine for use in aircraft > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,110,828 B2 - Document ID: US12110828B2 - Status: Granted - Kind: B2 - Application number: 18/250,938 - Filed: 2020-10-28 - Published: 2023-12-21 - Granted: 2024-10-08 - Earliest claimed: 2020-10-28 - Assignees: Kawasaki Jukogyo Kabushiki Kaisha - Applicants: Kawasaki Jukogyo Kabushiki Kaisha - Inventors: Hiroaki Takami; Naoya Sekoguchi; Katsuhiko Ishida; Kenta Umezaki; Hiroshi Sakamoto; Tatsuhiko Goi - Web page: https://patentgrep.com/patent/US12110828B2 ## CPC - F02C 7/32: Arrangement, mounting, or driving, of auxiliaries - B64D 41/00: Power installations for auxiliary purposes - F02K 3/06: with front fan - B64D 27/00: Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants - 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) - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN 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) - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A core engine including a core casing covering a low-pressure rotary structure and a high-pressure rotary structure and includes a passage of air flowing through the low-pressure and the high-pressure rotary structures; a fan located in front of the core engine; an inner cowl serving as an inner peripheral surface of a bypass passage that extends through the fan and bypasses the core engine; an accessory gear box that extracts power from the low-pressure or the high-pressure rotary structure and supplies the power to accessories; an auxiliary compressor attached to the accessory gear box, is driven by power of the accessory gear box, and increases pressure of compressed air extracted from the core engine; and a compressed air pipe that extends through an inside of a strut connecting the core engine and an airframe and supplies the compressed air having an increased pressure by the auxiliary compressor to the airframe. ## Claims ### Claim 1 A gas turbine engine for use in an aircraft, the gas turbine engine comprising: a core engine including a low-pressure rotary structure including a low-pressure compressor and a low-pressure turbine which are coupled to each other, a high-pressure rotary structure including a high-pressure compressor and a high-pressure turbine which are coupled to each other, and a core casing that covers the low-pressure rotary structure and the high-pressure rotary structure and includes a passage of air flowing through the low-pressure rotary structure and the high-pressure rotary structure; a fan located in front of the core engine; an inner cowl that serves as an inner peripheral surface of a bypass passage that extends through the fan and bypasses the core engine; an accessory gear box that extracts power from the low-pressure rotary structure or the high-pressure rotary structure and supplies the power to various accessories; an auxiliary compressor that is attached to the accessory gear box through a continuously variable transmission, is driven by driving power of the accessory gear box, and increases pressure of compressed air extracted from the core engine; and a compressed air pipe that extends through an inside of a strut connecting the core engine and an airframe and supplies to the airframe the compressed air that has been increased in pressure by the auxiliary compressor, wherein the continuously variable transmission changes a rotational speed of the accessory gear box, the accessory gear box and the auxiliary compressor are located in an inner space between the core casing and the inner cowl, the compressed air pipe extends toward the strut through a route that is shorter in distance to the strut between a route from the auxiliary compressor toward a right side in a circumferential direction along the core casing and a route from the auxiliary compressor toward a left side in the circumferential direction along the core casing; and the compressed air pipe then extends through the inside of the strut. ### Claim 2 (depends on 1) The gas turbine engine according to claim 1, wherein the auxiliary compressor is located in front of the accessory gear box in an axial direction of the core engine. ### Claim 3 (depends on 2) The gas turbine engine according to claim 2, wherein: the auxiliary compressor is located outside the low-pressure compressor or the high-pressure compressor in a radial direction; and an axial position of the auxiliary compressor overlaps an axial position of the low-pressure compressor or an axial position of the high-pressure compressor. ### Claim 4 (depends on 1) The gas turbine engine according to claim 1, wherein: the accessory gear box extends and curves in the circumferential direction along the core casing; the various accessories are attached to the accessory gear box so as to be lined up in the circumferential direction; and the auxiliary compressor is attached to a portion of the accessory gear box which is located closer to the strut than a circumferential middle portion of the accessory gear box. ### Claim 5 (depends on 4) The gas turbine engine according to claim 4, comprising an air starter that, when starting the gas turbine engine, is supplied with high-pressure air from the airframe through the compressed air pipe and rotates the gas turbine engine through the accessory gear box by using the supplied high-pressure air as a driving source, wherein the auxiliary compressor and the air starter are attached to the accessory gear box so as to be adjacent to each other in the circumferential direction or so as to sandwich the accessory gear box and face each other.