US 12,078,101 B2
Method for regulating a turbomachine comprising a temporary power-increasing device
Frédéric Gaétan Pousse, Moissy-Cramayel (FR); and Bertrand Yves Georges Moine, Moissy-Cramayel (FR)
Assigned to SAFRAN HELICOPTER ENGINES, Bordes (FR)
Appl. No. 17/605,898
Filed by SAFRAN HELICOPTER ENGINES, Bordes (FR)
PCT Filed Apr. 10, 2020, PCT No. PCT/EP2020/060332
§ 371(c)(1), (2) Date Oct. 22, 2021,
PCT Pub. No. WO2020/216639, PCT Pub. Date Oct. 29, 2020.
Claims priority of application No. 19 04310 (FR), filed on Apr. 24, 2019.
Prior Publication US 2022/0106908 A1, Apr. 7, 2022
Int. Cl. F02C 3/30 (2006.01); F02C 9/28 (2006.01)
CPC F02C 3/305 (2013.01) [F02C 9/28 (2013.01); F05D 2220/323 (2013.01); F05D 2220/329 (2013.01); F05D 2270/053 (2013.01); F05D 2270/16 (2013.01); F05D 2270/3062 (2013.01)] 13 Claims
OG exemplary drawing
 
1. A method for controlling a turbomachine configured to be assembled on an aircraft, the turbomachine comprising a temporary power-increasing device, said device comprising a reservoir configured to contain a coolant and an injection circuit configured to inject the coolant via an injection manifold upstream of at least one compressor stage of the turbomachine, a flow rate of injection of the coolant being variable, said controlling method comprising:
activating the temporary power-increasing device wherein the coolant is injected upstream of the at least one compressor stage of the turbomachine; and
controlling the flow rate of the coolant wherein the flow rate of the coolant injected is adjusted as a function of at least one of an atmospheric pressure and an ambient temperature,
wherein the temporary power-increasing device is activated if at least one of an instantaneous loss of power of the turbomachine is detected, entry into a predetermined rating of the turbomachine is detected, an additional power requirement is detected, and on request by a user, and
wherein the temporary power-increasing device is activated as a function of:
the following parameters of the turbomachine including a speed of rotation of a gas generator, a speed of rotation of a low-pressure turbine or of a power turbine, a gas pressure at an outlet of a compressor stage, a temperature at an inlet of the low-pressure turbine or of the power turbine, and an engine torque, and
at least one parameter of the aircraft for which the turbomachine is configured to be assembled selected among a collective pitch of the helicopter rotor or a pitch of a propeller of one or more turboprops.