Hybridisation of the compressors of a turbojet

Patent metadata

Field	Value
Publication number	US-11767794-B2
Application number	US-201515500792-A
Country	US
Kind code	B2
Filing date	Aug 4, 2015
Priority date	Aug 8, 2014
Publication date	Sep 26, 2023
Grant date	Sep 26, 2023

Abstract

A twin-flow, double body turbojet includes a fan that is positioned upstream from a gas generator and delimits primary and secondary flows. The gas generator is traversed by the primary flow and includes a low-pressure compressor, a high-pressure compressor, a combustion chamber, a high-pressure turbine and a low-pressure turbine. The low-pressure turbine is linked to the low-pressure compressor by a low-pressure rotating shaft, and the high-pressure turbine is linked to the high-pressure compressor by a high-pressure rotating shaft. The turbojet has an electric motor for injecting mechanical power into at least one of the rotating shafts. The turbojet also has a device for removing power from at least one of the rotating shafts and transforming the excess power into electrical energy. An electric storage means is positioned between the device for removing power and the electric motor.

First claim

The invention claimed is:

1. A twin-spool bypass turbojet engine comprising a fan positioned upstream from a gas generator and delimiting a primary flow and a secondary flow, the gas generator having the primary flow pass through the gas generator and comprising a low-pressure compressor, a high-pressure compressor, a combustion chamber, a high-pressure turbine and a low-pressure turbine,
the low-pressure turbine being connected to the low-pressure compressor by a low-pressure shaft and the high-pressure turbine being connected to the high-pressure compressor by a high-pressure shaft,
wherein the turbojet engine further comprises an electric motor configured to supply an applied mechanical power to at least one of the low-pressure and high-pressure shafts through a power application device, and an electric generator configured to draw an extracted mechanical power from at least one of the low-pressure and high-pressure shafts through a power take-off device,
wherein the power take-off device is sized to extract an excess mechanical power of the extracted mechanical power for actuating at least one auxiliary system of the turbojet engine, the electric generator transforming the excess mechanical power into an electrical energy,
wherein the electrical energy is transformed into the applied mechanical power by the electric motor for actuating at least one of the low-pressure and high-pressure shafts,
wherein an electricity storage device is operably connected to the power take-off device and the electric motor, the electric storage device being configured to store the electrical energy,
wherein the excess mechanical power being drawn by the power take-off device from the low-pressure shaft and the applied mechanical power being supplied to the high-pressure shaft by the power application device during an operation of the turbojet engine,
wherein a first portion of the low-pressure shaft is selectively coupled to a fan driveshaft which is a second portion of the low-pressure shaft to provide a coupled state and an uncoupled state, the power take-off device being configured to draw a fan mechanical power from the fan driveshaft when the first portion of the low-pressure shaft and the fan driveshaft are in the uncoupled state, and
wherein the fan mechanical power is applied to the high-pressure shaft when the first portion of the low-pressure shaft and the fan driveshaft are in the uncoupled state.

2. The twin-spool bypass turbojet engine according to claim 1 , wherein the electric motor is connected to the power take-off device and meshes on at least one of the low-pressure shaft and the high-pressure shaft through the power application device to provide the applied mechanical power during a normal operation of the turbojet engine.

3. The twin-spool bypass turbojet engine according to claim 2 , wherein the electricity storage device is connected in parallel between the power take-off device and the electric motor.

4. The twin-spool bypass turbojet engine according to claim 1 , wherein the applied mechanical power is performed at a rotation speed of the high-pressure shaft greater than or equal to 80% of a high-pressure shaft rotation speed at full throttle.

5. The twin-spool bypass turbojet engine according to claim 1 , wherein the applied mechanical power is performed at an in-flight idling speed.

6. The twin-spool bypass turbojet engine according to claim 1 , wherein the electrical energy stored in the electricity storage device powers the electric motor to provide the applied mechanical power to the high-pressure shaft.

7. The twin-spool bypass turbojet engine according to claim 1 , wherein, during a normal operation of the turbojet engine, said applied mechanical power is supplied directly to the high-pressure shaft, through the electric motor.

8. The twin-spool bypass turbojet engine according to claim 1 , wherein the power application device and the power take-off device are drive shafts which are meshed on at least one of the low-pressure and high-pressure shafts.

9. The twin-spool bypass turbojet engine according to claim 1 , wherein the power application device is independent and separate from the power take-off device.

10. The twin-spool bypass turbojet engine
according to claim 1 , wherein
the power take-off device is configured to:
in a first case, when the excess mechanical power is greater than a power requirement of the high-pressure shaft, said excess mechanical power is distributed between a first value chosen by a designer of the twin-spool bypass turbojet engine for improving the surge margin at an operating point; and a second value excess that is sent to the electricity storage device, and
in a second case contrary to the first case, when said excess mechanical power extracted on the low-pressure shaft is less that the first value, a quantity of energy is destocked from the electricity storage device for a transmission of said quantity of energy to the electric motor.

Assignees

• Safran Aircraft Engines

Inventors

• Robic Bernard
• Obrecht Thierry Jean-Jacques
• Renault Baptiste Jean Marie

Classifications

• F02C7/32 Primary

  Arrangement, mounting, or driving, of auxiliaries · CPC title

• F02C7/36

  Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user ({F02C3/107 - F02C3/13 and} F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H) · CPC title

• F02K3/06 Primary

  with front fan · CPC title

• F05D2220/76

  an electrical generator · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title