US 12,392,282 B2
Constant volume combustor for gas turbine engine
Dave Menheere, Norval (CA)
Assigned to PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed by Pratt & Whitney Canada Corp., Longueuil (CA)
Filed on Mar. 28, 2023, as Appl. No. 18/127,155.
Prior Publication US 2024/0328349 A1, Oct. 3, 2024
Int. Cl. F02C 5/08 (2006.01); F23R 7/00 (2006.01)
CPC F02C 5/08 (2013.01) [F23R 7/00 (2013.01); F05D 2240/35 (2013.01)] 17 Claims
OG exemplary drawing
 
1. 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.