# US 12,000,294 B2 · Power withdrawal from a LP body and system for removing debris > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,000,294 B2 - Document ID: US12000294B2 - Status: Granted - Kind: B2 - Application number: 17/440,380 - Filed: 2020-03-18 - Published: 2022-05-19 - Granted: 2024-06-04 - Earliest claimed: 2019-03-18 - Assignees: Safran Aircraft Engines - Applicants: Safran Aircraft Engines - Inventors: Nicolas Bertrand Georges De Blois; Clément Dupays - Web page: https://patentgrep.com/patent/US12000294B2 ## CPC - F01D 25/002: {Cleaning of turbomachines} - F02C 9/18: by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)} - F02C 7/32: Arrangement, mounting, or driving, of auxiliaries - F02K 3/02: in which part of the working fluid by-passes the turbine and combustion chamber - F05D 2220/323: for aircraft propulsion, e.g. jet engines - F05D 2220/76: an electrical generator - F05D 2260/607: Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles - F05D 2270/023: of different spools or shafts - F05D 2270/101: Compressor surge or stall - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - 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) - 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 The invention concerns a bypass turbomachine (1) with a primary flow path and a secondary flow path, comprising: —a low-pressure body comprising a low-pressure compressor (120) connected to a low-pressure turbine (122) via a low-pressure shaft (124), —a high-pressure body comprising a high-pressure compressor (130) connected to a high pressure turbine (132), via a high-pressure shaft (134), —a low-pressure power take-off system (220) comprising an electrical generator (226), configured to take power (W12) from the low-pressure body, wherein—the turbomachine comprises a debris removal system (500), located between the two compressors (226, 236), —the low-pressure power take-off system (220) is configured to take power (W12) from the low-pressure shaft (124) using the resistive torque of the electrical generator (226), in order to avoid a risk of surging. ## Claims ### Claim 1 A bypass gas turbine engine comprising: a low-pressure spool comprising a low-pressure compressor connected to a low-pressure turbine via a low-pressure shaft; a high-pressure spool comprising a high-pressure compressor connected to a high-pressure turbine via a high-pressure shaft; a low-pressure power withdrawal system comprising an electrical generator and configured to withdraw power from the low-pressure spool, wherein the low-pressure power withdrawal system is configured to withdraw power from the low-pressure shaft using a resistive torque of the electrical generator on a withdrawal command of an electronic control unit to slow down the low-pressure compressor and avoid a surge between the high-pressure compressor and the low-pressure compressor; a debris detection device configured to detect a presence of debris between the low-pressure compressor and the high-pressure compressor; and a debris expulsion system located between the low-pressure compressor and the high-pressure compressor, wherein the debris expulsion system comprises at least one door being opened only when the debris detection device detects a debris. ### Claim 2 (depends on 1) The gas turbine engine of claim 1, wherein the debris expulsion system is further configured to be activated when hail or water is ingested, on command of the electronic control unit. ### Claim 3 (depends on 1) The gas turbine engine of claim 1, wherein the power withdrawal is configured to be controlled as a function of rotational speed of the low-pressure compressor and of the high-pressure compressor, on command of the electronic control unit. ### Claim 4 (depends on 3) The gas turbine engine of claim 3, wherein the electronic control unit controls the power withdrawal as a function of an instantaneous variations of rotational speed of the low-pressure compressor and of the high-pressure compressor. ### Claim 5 (depends on 1) The gas turbine engine of claim 1, wherein the at least one door is opened in a go no-go arrangement. ### Claim 6 (depends on 1) The gas turbine engine of claim 1, wherein the debris expulsion system is further configured to be controlled in a go no-go arrangement, on command of the electronic control unit. ### Claim 7 (depends on 1) The gas turbine engine of claim 1, further comprising a dedicated electronic control unit, separate from the electronic control unit of the gas turbine engine, and configured to control the power withdrawal as a function of an instantaneous variations of rotational speed of the low-pressure compressor and of the high-pressure compressor, on command of the electronic control unit. ### Claim 8 (depends on 1) The gas turbine engine of claim 1, wherein the debris expulsion system is further configured to be controlled in a go no-go arrangement, on command of the electronic control unit, in an event of a failure to maintain a surge margin through the low-pressure power withdrawal system, to expel an overpressure between the low-pressure compressor and the high-pressure compressor. ### Claim 9 (depends on 1) A propulsion assembly for an aircraft, comprising the gas turbine engine of claim 1 and the electronic control unit able to generate the withdrawal command to slow down the low-pressure compressor.