Augmentor liner construction
An augmentor for a gas turbine engine is described having a gas path for flowing the engine's working medium including a generally circular shaped duct, a variable nozzle attached to the end of the duct in proximity to the engine's working medium exiting from the duct, a generally circular shaped linear attached to the end of the engine concentrically disposed relative to the duct and defining an open ended annular flow path for receiving cooling air between the engine's liner and the duct. The liner terminating is in proximity to the exit plane of the duct. The improvement comprises an annular, circumferentially disposed sinusoidally shaped member attached to the end of the liner adjacent the exit end of the duct and extending radially outwardly relative to the engine's working medium and defining open ended passageways, a separate end piece supported to the duct in proximity to the sinusoidal member for distributing the cooling air discharging from the open ended annular flow path and the open ended passageways of the sinusoidally shaped member to the nozzle for defining a uniform flow path around the circumference of the nozzle. To support the liner, one end of the separate end piece providing an abutment for supporting the sinusoidally shaped member when the sinusoidally shaped member is expanded by the engine working medium and the separate end piece extending axially beyond the exit end of the duct and defining with the duct an annular gap having a predetermined annular dimension for providing a predetermined amount of cooling air to flow to the nozzle throughout the operating range of the augmentor.
- Assignee:
- United Technologies Corp., Hartford, CT
- Patent Number(s):
- US 4718230
- OSTI ID:
- 5280395
- Resource Relation:
- Patent File Date: Filed date 10 Nov 1986
- Country of Publication:
- United States
- Language:
- English
Similar Records
Cooling scheme for combustor vane interface
Combustor bulkhead heat shield assembly