F02C9/18

SYSTEM AND METHOD FOR CONTROLLING LOW PRESSURE RECOUP AIR IN GAS TURBINE ENGINE

Control of low pressure recoup air in a gas turbine engine disposed in a gas turbine enclosure with low pressure recoup air piping coupled to a gas turbine combustion exhaust and gas turbine engine enclosure is disclosed. A first valve of the piping controls a flow of the recoup air to the gas turbine combustion exhaust. A second valve of the piping diverts the recoup air to the enclosure for eventual flow to the air intake. A controller controls the flow of the recoup air from the piping to the exhaust and/or the enclosure as a function of ambient and air intake temperature measurements, and a predetermined temperature requirement having an ambient temperature constraint and an air intake temperature differential constraint.

METHODS AND SYSTEMS FOR OPERATING AN ENGINE TO GENERATE ADDITIONAL THRUST
20230046718 · 2023-02-16 ·

Methods and systems for operating an engine, the engine having an engine core, an exhaust nozzle, and variable geometry mechanisms, are provided. A request for an increase in thrust generated by the engine is received. In response to receipt of the request, it is determined that at least one operating condition for engine degradation thrust is met. In response to this determination, the variable geometry mechanisms are modulated to degrade an efficiency of the engine, thereby increasing a temperature of core air flowing through the engine core. The increase in thrust is generated from the increased temperature of the core air flowing through the engine core and into the exhaust nozzle.

METHODS AND SYSTEMS FOR OPERATING AN ENGINE TO GENERATE ADDITIONAL THRUST
20230046718 · 2023-02-16 ·

Methods and systems for operating an engine, the engine having an engine core, an exhaust nozzle, and variable geometry mechanisms, are provided. A request for an increase in thrust generated by the engine is received. In response to receipt of the request, it is determined that at least one operating condition for engine degradation thrust is met. In response to this determination, the variable geometry mechanisms are modulated to degrade an efficiency of the engine, thereby increasing a temperature of core air flowing through the engine core. The increase in thrust is generated from the increased temperature of the core air flowing through the engine core and into the exhaust nozzle.

TURBOMACHINE WITH DEVICE FOR COOLING AND PRESSURISING A TURBINE
20230048118 · 2023-02-16 ·

The invention relates to a turbomachine comprising a device for ventilating and pressurising a turbine rotor of a turbomachine of axis (A), the device comprising at least one collection pipe suitable for collecting a fraction of the air circulating in a high-pressure compressor of the turbomachine and conveying it to a first inner chamber (39) inside the turbomachine that communicates with a second inner chamber (40) delimited by the turbine (24) rotor (23), the first and second chambers (39, 40) being at least partially separated by a stationary shroud (56) of axis (A), characterised in that it comprises at least one injector (58) passing through the stationary shroud (56) and having a cross-section that varies in response to a pressure difference between said first and second chambers (39, 40).

COMBINED POWER SYSTEM
20230047728 · 2023-02-16 ·

A compressor wheel is provided for the output shaft. Air bleed ports are formed in a shroud case that surrounds the compressor wheel. A plurality of air bleed passages are formed in the engine housing that surrounds the shroud case. An annular chamber is formed between the air bleed ports and the air bleed passages, for storing compressed air that is extracted from the air bleed ports.

COMBINED POWER SYSTEM
20230047728 · 2023-02-16 ·

A compressor wheel is provided for the output shaft. Air bleed ports are formed in a shroud case that surrounds the compressor wheel. A plurality of air bleed passages are formed in the engine housing that surrounds the shroud case. An annular chamber is formed between the air bleed ports and the air bleed passages, for storing compressed air that is extracted from the air bleed ports.

COMBINED POWER SYSTEM
20230053171 · 2023-02-16 ·

In a rotary electric machine housing, a first bearing and a second bearing are provided for supporting a rotating shaft. A lubricating oil is supplied to the first bearing and the second bearing. At least one of the first bearing or the second bearing is sandwiched between the compressed air supplied from one side of the rotating shaft in an axial direction thereof and the compressed air supplied from another side of the rotating shaft in the axial direction.

COMBINED POWER SYSTEM
20230053171 · 2023-02-16 ·

In a rotary electric machine housing, a first bearing and a second bearing are provided for supporting a rotating shaft. A lubricating oil is supplied to the first bearing and the second bearing. At least one of the first bearing or the second bearing is sandwiched between the compressed air supplied from one side of the rotating shaft in an axial direction thereof and the compressed air supplied from another side of the rotating shaft in the axial direction.

Method and system for operating a gas turbine engine

A system has: a combustor; a plenum surrounding the combustor; a transfer tube having an inlet fluidly connected to the plenum and at least two outlets, a first flow passageway defined between the inlet and a first outlet, a second flow passageway defined between the inlet and a second outlet, the second flow passageway connected to a discharge region outside of the plenum; a flow valve disposed within the second flow passageway and operable between an open position and a closed position, in the open position the flow valve fluidly connects the plenum with the discharge region, in the closed position the flow valve blocking fluid communication between the plenum and the discharge region; and a controller communicatively coupled to the flow valve to control operation thereof by: causing the flow valve to open for a time period; and subsequent to the time period, causing the flow valve to close.

Method and system for operating a gas turbine engine

A system has: a combustor; a plenum surrounding the combustor; a transfer tube having an inlet fluidly connected to the plenum and at least two outlets, a first flow passageway defined between the inlet and a first outlet, a second flow passageway defined between the inlet and a second outlet, the second flow passageway connected to a discharge region outside of the plenum; a flow valve disposed within the second flow passageway and operable between an open position and a closed position, in the open position the flow valve fluidly connects the plenum with the discharge region, in the closed position the flow valve blocking fluid communication between the plenum and the discharge region; and a controller communicatively coupled to the flow valve to control operation thereof by: causing the flow valve to open for a time period; and subsequent to the time period, causing the flow valve to close.