Supercharging systems for aircraft engines

Patent metadata

Field	Value
Publication number	US-2019323426-A1
Application number	US-201815957573-A
Country	US
Kind code	A1
Filing date	Apr 19, 2018
Priority date	Apr 19, 2018
Publication date	Oct 24, 2019
Grant date	—

Abstract

Supercharging systems for aircraft engines are described herein. An example supercharging system includes an ejector disposed in a core air intake of a gas turbine engine. The core air intake is to direct air into a compressor of the gas turbine engine. The supercharging system also includes a compressed air tank containing pressurized air. The compressed air tank is fluidly coupled to the ejector. The ejector is to provide the pressurized air into the core air intake to increase output power of the gas turbine engine.

First claim

What is claimed is:

1 . A supercharging system for a gas turbine engine of an aircraft, the supercharging system comprising:
an ejector disposed in a core air intake of the gas turbine engine, the core air intake to direct air into a compressor of the gas turbine engine; and a compressed air tank containing pressurized air, the compressed air tank fluidly coupled to the ejector, the ejector to provide the pressurized air into the core air intake to increase output power of the gas turbine engine.

2 . The supercharging system of claim 1 , wherein the core air intake is defined by an outer radial wall and an inner radial wall, and wherein the ejector includes a plurality of struts extending between the outer radial wall and the inner radial wall, the struts having openings facing downstream to eject the pressurized air into the gas turbine engine.

3 . The supercharging system of claim 1 , further including:
a supply line coupled between the compressed air tank and the ejector; and a valve coupled to the supply line to control a flow of the pressurized air from the compressed air tank to the ejector.

4 . The supercharging system of claim 3 , further including a controller configured to:
based on an input signal requesting to increase the output power of the gas turbine engine, send a command signal to open the valve to enable the flow of the pressurized air from the compressed air tank to the ejector and into the compressor of the gas turbine engine.

5 . The supercharging system of claim 4 , wherein the valve is a pressure reducing shutoff valve, and wherein the controller is configured to, based on a desired output power level of the gas turbine engine, operate the valve to reduce a pressure of the pressurized air to a target pressure value.

6 . The supercharging system of claim 5 , further including a pressure sensor coupled to the supply line, and wherein the controller is configured to operate the valve based on a pressure measurement obtained by the pressure sensor.

7 . The supercharging system of claim 4 , wherein the command signal is a first command signal, and wherein the controller is configured to, after sending the first command signal to open the valve, send a second command signal to close a damper that is disposed in the core air intake upstream from the ejector, the damper operable to block airflow through the core air intake.

8 . The supercharging system of claim 1 , wherein the compressed air tank forms at least a portion of an aft pressure bulkhead in a fuselage of an aircraft.

9 . A method of increasing output power of an aircraft engine, the method comprising:
receiving, at a controller, an input signal requesting to increase output power of a gas turbine engine of an aircraft via a supercharging system, the supercharging system including a compressed air tank having pressurized air, an ejector disposed in a core air intake of the gas turbine engine, and a valve between the compressed air tank and the ejector; determining, via the controller, whether one or more parameters are satisfied; and sending, via the controller, a command signal to open the valve based on the determination that the one or more parameters are satisfied, the valve, when opened, enables a flow of the pressurized air from the compressed air tank, through the ejector and into the gas turbine engine.

10 . The method of claim 9 , further including operating, via the controller, the valve to reduce a pressure of the pressurized air to a target pressure value based on pressure measurements from one or more pressure sensors.

11 . The method of claim 10 , wherein the target pressure value is based on a desired output power level received by the controller.

12 . The method of claim 9 , wherein the command signal is a first command signal, further including, after sending the first command signal to open the valve, sending, via the controller, a second command signal to a damper to change a state of the damper from an open state to a closed state, the damper disposed in the core air intake upstream of the ejector.

13 . The method of claim 9 , wherein the input signal is a first input signal and the command signal is a first command signal, further including:
receiving, at the controller, a second input signal requesting to cease supplying the pressurized air to the gas turbine engine; and sending, via the controller, a second command signal to close the valve in response to the second input signal.

14 . The method of claim 13 , further including, prior to sending the second command signal:
determining, via the controller, whether a damper disposed in the core air intake has been opened.

15 . An aircraft comprising:
a hybrid propulsion engine having a gas turbine engine, an electric motor, and a propulsor, the gas turbine engine to drive the propulsor during a first mode of operation and the electric motor to drive the propulsor during a second mode of operation; and a supercharging system to inject pressurized air into the gas turbine engine for producing increased output power while the hybrid propulsion engine is operating in the first mode of operation.

16 . The aircraft of claim 15 , wherein the supercharging system includes a compressed air tank containing the pressurized air and an ejector disposed in a core air intake of the gas turbine engine.

17 . The aircraft of claim 15 , further including a controller configured to:
activate the supercharging system to inject the pressurized air into the gas turbine engine for a period of time; and deactivate the supercharging system to cease injection of the pressurized air after the period of time.

18 . The aircraft of claim 17 , wherein the controller is configured to:
after deactivation of the supercharging system, send command signals to start the electric motor and shut down the gas turbine engine to switch the hybrid propulsion engine from the first mode of operation to the second mode of operation.

19 . The aircraft of claim 17 , further including a core damper disposed in a core air intake of the gas turbine engine, and wherein the controller is configured to move the core damper to a closed state to block the core air intake while the supercharging system is injecting the pressurized air into the gas turbine engine.

20 . The aircraft of claim 19 , wherein the controller is configured to move the core damper to an open state prior to deactivating the supercharging system.

Assignees

• Boeing Co

Inventors

• Mackin Steve G

Classifications

• F02C7/057

  Control or regulation (conjointly with fuel supply control F02C9/50, with nozzle area control F02K1/16) · CPC title

• F02C7/04

  Air intakes for gas-turbine plants or jet-propulsion plants · CPC title

• B64D27/10

  of gas-turbine type  (jet aircraft B64D27/16) · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F02C9/20

  by throttling; by adjusting vanes · CPC title