US 12,392,282 B2Granted

Constant volume combustor for gas turbine engine

AssigneePratt & Whitney Canada Corp.

InventorDave Menheere

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Abstract

A combustor assembly for a turbine engine includes a combustor assembly where a first combustion space is defined between a first closed end of a combustion chamber and a first piston, a second combustion space is defined between a second closed end of the combustion chamber and a second piston and a center combustion space is defined between the first piston and the second piston. An air inlet assembly provides for communication of inlet air to the first combustion space, the second combustion space and the center combustion space. First, second and center injectors are provided to inject fuel into a corresponding one of the first combustion space, the second combustion space, and the center combustion space. An exhaust outlet communicates an exhaust gas flow generated in each of the first combustion space, the second combustion space and the center combustion space to a turbine section.

Claims17

Dependent claims

A combustor assembly for a turbine engine, the combustor assembly comprising:

at least one combustion chamber closed at a first end and at a second end;
a first piston and a second piston moveable independent of each other within the combustion chamber, wherein a first combustion space is defined between the first end and the first piston, a second combustion space is defined between the second end and the second piston and a center combustion space is defined between the first piston and the second piston;
an air inlet assembly where an inlet airflow is communicated to the first combustion space, the second combustion space and the center combustion space;
a first injector configured to inject fuel into the first combustion space;
a second injector configured to inject fuel in to the second combustion space;
a center injector configured to inject fuel into the center combustion space, wherein the center combustion space is configured to combust a fuel air mixture to drive the first piston and the second piston apart toward a corresponding one of the first combustion space and the second combustion space;
and
an exhaust outlet assembly for receiving an exhaust gas flow generated in each of the first combustion space, the second combustion space and the center combustion space.

5 more elements

A turbine engine assembly comprising:

a compressor section where inlet air is compressed to generate a core airflow;
a combustor assembly where the core airflow is mixed with fuel and ignited to generate an exhaust gas flow, wherein the combustor assembly includes at least one combustion chamber closed at a first end and at a second end and a first piston and a second piston that are both movable independent of each other within the combustion chamber, wherein a first combustion space is defined between the first end and the first piston, a second combustion space is defined between the second end and the second piston and a center combustion space is defined between the first piston and the second piston, wherein the center combustion space is configured to combust a fuel air mixture to drive the first piston and the second piston apart toward a corresponding one of the first combustion space and the second combustion space;
and
a turbine section where the exhaust gas flow from the combustor assembly is expanded to generate shaft power.

1 more element

Dependencies are inferred from the claim text.