Impeller back-face cooling aperture
AssigneePratt & Whitney Canada Corp.
InventorsPatrice Remy, Ian Macfarlane
Life of this patent
Estimating the term…
Abstract
A nozzle of a diffuser baffle of a compressor section of a gas turbine engine of an aircraft includes a body having circumferentially arced inboard and outboard surfaces, radially oriented side surfaces and forward and aft facing major surfaces. The body includes a baffle attached to the aft facing major surface. The baffle has a baffle surface angled relative to the aft facing major surface. The body defines an aperture, which extends through and which is angled relative to the forward and aft facing major surfaces, to define an angled flow path upstream from the baffle whereby fluid flowing through the angled flow path is directed tangentially toward and then deflected by the baffle surface.
Claims20
A nozzle of a diffuser baffle of a compressor section of a gas turbine engine of an aircraft, the nozzle comprising:
- a body having circumferentially arced inboard and outboard surfaces, radially oriented side surfaces and forward and aft facing major surfaces,
- the body comprising a baffle attached to the aft facing major surface, the baffle having a baffle surface angled relative to the aft facing major surface, and
- the body defining an aperture, which extends through and which is angled relative to the forward and aft facing major surfaces, to define an angled flow path upstream from the baffle whereby fluid flowing through the angled flow path is directed tangentially toward and then deflected by the baffle surface.
A compressor section of a gas turbine engine of an aircraft, the compressor section comprising:
- an impeller;
- a diffuser baffle proximate to the impeller, whereby the impeller and the diffuser baffle define an intervening cavity therebetween;
- a nozzle installed in the diffuser baffle and configured to direct a flow of coolant into the intervening cavity in a direction comprising circumferential and axial directional components;
- and
- piping extending through the diffuser baffle and terminating in the nozzle to deliver the flow of the coolant to the nozzle.
A compressor section of a gas turbine engine of an aircraft, the compressor section comprising:
- an impeller comprising an impeller front-face along which high-temperature air flows and an impeller back-face opposite the impeller front-face;
- a diffuser baffle proximate to the impeller, whereby the impeller back-face and the diffuser baffle define an intervening cavity therebetween;
- a nozzle installed in the diffuser baffle and configured to direct a flow of coolant into the intervening cavity and tangentially toward the impeller back-face in a direction comprising circumferential and axial directional components;
- and
- piping extending through the diffuser baffle and terminating in the nozzle to deliver the flow of the coolant to the nozzle.
Dependencies are inferred from the claim text.