US 11,891,958 B2
Method and device for estimating a dead zone of a turbomachine discharge valve
Sébastien Jean Fernand Deneuve, Moissy-Cramayel (FR); and Jérôme Pascal Laurent Patrick Tronche, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/609,867
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed May 15, 2020, PCT No. PCT/EP2020/063596
§ 371(c)(1), (2) Date Nov. 9, 2021,
PCT Pub. No. WO2020/229655, PCT Pub. Date Nov. 19, 2020.
Claims priority of application No. 1905102 (FR), filed on May 16, 2019.
Prior Publication US 2022/0213841 A1, Jul. 7, 2022
This patent is subject to a terminal disclaimer.
Int. Cl. F02C 9/18 (2006.01); F02C 6/08 (2006.01); F02C 9/16 (2006.01); B64D 31/00 (2006.01)
CPC F02C 9/18 (2013.01) [B64D 31/00 (2013.01); F02C 6/08 (2013.01); F02C 9/16 (2013.01)] 8 Claims
OG exemplary drawing
 
1. A method for estimating a closing dead zone of a first gate of a first discharge valve mounted on a first casing of a turbomachine to be investigated, which can operate in flight to propel an aircraft, the first casing delimiting in its inside a first primary gas flow of the turbomachine, the first gate being designed to be able to be moved angularly by a first actuator depending on a first control signal of the first actuator between one and the other of:
a first opening position of a first orifice of the first casing configured to discharge by this first orifice a portion of the first primary gas flow into a first secondary gas flow located outside the first casing,
and a first closing position of the first orifice configured to prevent the first primary gas flow from passing through the first orifice,
the first gate being provided with a first gas seal gasket, able to be compressed against a first edge of the first orifice in the first closing position to seal closing of the first orifice,
the method comprising:
measuring, for the turbomachine to be investigated, operating in flight, a first actual position of the first actuator when the first control signal is equal to a first set point closing signal of the first gate,
determining, based on the first actual position, a measured droop angle of the first gate with respect to the first casing, and
determining for the turbomachine to be investigated, operating in flight, a measured closing dead zone of the first gate, in which the first gas seal gasket remains compressed and thus seals closing the first orifice, by the fact that the measured closing dead zone is equal to a reference dead zone, which was predetermined during operation on the ground on a reference turbomachine which can operate in flight and on the ground, to which has been added the measured droop angle and from which has been subtracted a reference droop angle which was predetermined on the reference turbomachine operating in flight to propel an aircraft.