US 12,000,294 B2
Power withdrawal from a LP body and system for removing debris
Nicolas Bertrand Georges De Blois, Moissy-Cramayel (FR); and Clément Dupays, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/440,380
Filed by Safran Aircraft Engines, Paris (FR)
PCT Filed Mar. 18, 2020, PCT No. PCT/EP2020/057497
§ 371(c)(1), (2) Date Sep. 17, 2021,
PCT Pub. No. WO2020/188000, PCT Pub. Date Sep. 24, 2020.
Claims priority of application No. 1902732 (FR), filed on Mar. 18, 2019.
Prior Publication US 2022/0154596 A1, May 19, 2022
Int. Cl. F01D 25/00 (2006.01); F02K 3/02 (2006.01)
CPC F01D 25/002 (2013.01) [F02K 3/02 (2013.01); F05D 2220/323 (2013.01)] 9 Claims
OG exemplary drawing
 
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.