High temperature disk conditioning system

Patent metadata

Field	Value
Publication number	US-10823085-B2
Application number	US-201815979906-A
Country	US
Kind code	B2
Filing date	May 15, 2018
Priority date	Jul 25, 2014
Publication date	Nov 3, 2020
Grant date	Nov 3, 2020

Abstract

A gas-circulation system for conditioning a disk of an aircraft may comprise a first takeoff port configured to extract a combusted gas and a second takeoff port configured to extract an uncombusted gas. A first valve may comprise an inlet in fluid communication with the first and second takeoff ports and an outlet of the first valve in fluid communication with the disk.

First claim

What is claimed is:

1. A gas-circulation system for conditioning a compressor disk of an aircraft, the gas-circulation system comprising:
a non-transitory memory communicating with a controller, the non-transitory memory having instructions stored thereon that, in response to execution by the controller, cause a processor to perform operations comprising:
commanding, by the controller, an actuator to open and close a valve that outputs a mixed gas with a desired temperature to heat a portion of the compressor disk proximate to a bore of the compressor disk, the valve comprising a mixing valve, wherein the mixed gas comprises an uncombusted gas and a combusted gas;
determining, by the controller, an engine speed;
comparing, by the controller, the engine speed to closing criteria; and
concluding, by the controller, that a failure occurred in the valve if a state of the valve is open in response to the engine speed being within the closing criteria.

2. The gas-circulation system of claim 1 , wherein the instructions further comprise:
determining, by the controller, an operational state of the aircraft; and
commanding, by the controller, the actuator to open the valve in response to the operational state corresponding to a predetermined operational state.

3. The gas-circulation system of claim 1 , wherein the instructions further comprise commanding, by the controller, the actuator to close the valve in response to the engine speed matching the closing criteria.

4. The gas-circulation system of claim 1 , wherein the instructions further comprise determining the state of the valve in response to a measurement from a thermocoupling.

5. The gas-circulation system of claim 1 , wherein the instructions further comprise responding, by the controller, to the failure by closing a check valve.

6. The gas-circulation system of claim 1 , wherein the closing criteria comprises a speed above a ground idle.

7. The gas-circulation system of claim 1 , wherein the instructions further comprise responding to the failure by reducing the engine speed to a ground idle.

8. The gas-circulation system of claim 1 , wherein the instructions further comprise monitoring the state of the valve.

9. The gas-circulation system of claim 1 , wherein the instructions further comprise cycling the valve before a flight.

10. A non-transitory, computer readable storage medium bearing instructions for conditioning a compressor, the instructions, when executed by a processor, cause said processor to perform operations comprising:
commanding an actuator to open and close a valve that outputs a mixed gas with a desired temperature to heat a portion of the compressor disk proximate to a bore of the compressor disk, the valve comprising a mixing valve, wherein the mixed gas comprises an uncombusted gas and a combusted gas;
determining an engine speed;
comparing the engine speed to closing criteria; and
concluding that a failure occurred in the valve if a state of the valve is open in response to the engine speed being within the closing criteria.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Schwarz Frederick M
• Forcier Matthew P

Classifications

• F02C3/34

  with recycling of part of the working fluid, i.e. semi-closed cycles with combustion products in the closed part of the cycle · CPC title

• F02C9/18 Primary

  by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)} · CPC title

• F02C7/125

  by partial arc admission of the working fluid or by intermittent admission of working and cooling fluid · CPC title

• Y02T50/60

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

• F01D25/10

  Heating, e.g. warming-up before starting · CPC title