Gas turbine engine with compressor bleed system for combustor start assist

Patent metadata

Field	Value
Publication number	US-11946474-B2
Application number	US-202117450840-A
Country	US
Kind code	B2
Filing date	Oct 14, 2021
Priority date	Oct 14, 2021
Publication date	Apr 2, 2024
Grant date	Apr 2, 2024

Abstract

A gas turbine engine includes a combustor having a combustor air inlet, an axial-centrifugal compressor, a shroud, a secondary flow duct, and a valve. The shroud surrounds at least a portion of the axial-centrifugal compressor and has a surge bleed plenum defined therein that is in fluid communication with, and receives compressed air from, the axial compressor outlet. The secondary airflow duct has a duct inlet that is in fluid communication with the surge bleed plenum, and a duct outlet that is in fluid communication with the combustor air inlet. The valve is mounted on the secondary airflow duct and is movable between a closed position, in which the secondary airflow duct does not provide fluid communication between the surge bleed plenum and the combustor air inlet, and an open position, in which the secondary airflow duct provides fluid communication between the surge bleed plenum and the combustor air inlet.

First claim

What is claimed is:

1. A method of controlling compressed airflow in a gas turbine engine that includes a combustor, an axial-centrifugal compressor disposed upstream of the combustor and having an axial compressor and a centrifugal compressor, and a shroud that surrounds at least a portion of the axial compressor and has a surge bleed plenum defined therein, wherein the combustor has a combustor air inlet, wherein the axial compressor has an axial compressor inlet and an axial compressor outlet, wherein the centrifugal compressor has a centrifugal compressor inlet in fluid communication with the axial compressor outlet and a centrifugal compressor outlet in fluid communication with the combustor air inlet, and wherein the surge bleed plenum is in fluid communication with, and receives compressed air from, the axial compressor outlet, the method comprising the steps of:
providing a secondary airflow duct having a duct inlet and a duct outlet, where the duct inlet is in continuous fluid communication with the surge bleed plenum and the duct outlet is in continuous fluid communication with the combustor air inlet; and
selectively moving a valve that is mounted on the secondary airflow duct between a closed position, in which compressed air from the axial compressor outlet cannot flow, via the surge bleed plenum, through the secondary airflow duct and into the combustor air inlet, and at least one open position, in which compressed air from the axial compressor outlet flows, via the surge bleed plenum, through the secondary airflow duct and into the combustor air inlet.

2. The method of claim 1 , wherein the step of selectively moving the valve comprises supplying valve position commands to a valve actuator that is coupled to the valve and that is responsive, to the valve position commands, to move the valve between the closed position and the at least one open position.

3. The method of claim 2 , wherein the valve actuator is selected from the group consisting of an electrical actuator, a hydraulic actuator, a pneumatic actuator, an electrohydraulic actuator, and an electropneumatic actuator.

4. The method of claim 2 , further comprising:
supplying the valve position commands to the valve actuator from a controller that is in operable communication with the valve actuator.

5. The method of claim 4 , wherein the controller is an engine controller.

6. The method of claim 4 , further comprising:
supplying sensor signals, each indicative of a sensed engine parameter, from a plurality of sensors disposed within the gas turbine engine to the controller.

7. The method of claim 1 , wherein the valve is a pressure actuated check valve.

8. The method of claim 1 , wherein the axial compressor comprises a plurality of axial stages.

9. The method of claim 8 , wherein each of the plurality of axial stages comprises at least one stator assembly and a rotor assembly operably coupled to a shaft assembly for rotation relative to the stator assembly.

10. The method of claim 9 , wherein at least two of the plurality of blade assemblies are coupled for co-rotation on the shaft assembly.

11. The method of claim 1 , wherein a shaft assembly is operably coupled to the axial compressor and the centrifugal compressor for co-rotation thereof.

12. The method of claim 11 , wherein:
the axial compressor comprises a plurality of axial stages; and
at least one of the plurality of axial stages is coupled for co-rotation with the centrifugal compressor section.

Assignees

• Honeywell Int Inc

Inventors

• Reynolds Bruce David
• Nolcheff Nick
• Mansour Mahmoud
• Darling Timothy
• Kurschat Ernest

Classifications

• F04D17/025 Primary

  comprising axial flow and radial flow stages · CPC title

• F01D17/26

  fluid, e.g. hydraulic · CPC title

• F01D19/00

  Starting of machines or engines; Regulating, controlling, or safety means in connection therewith (warming-up before starting F01D25/10; turning or inching gear F01D25/34) · CPC title

• F02C7/264

  Ignition · CPC title

• F02C9/18

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