Gas turbine engine ejector

Patent metadata

Field	Value
Publication number	US-10197009-B2
Application number	US-201414514770-A
Country	US
Kind code	B2
Filing date	Oct 15, 2014
Priority date	Jul 30, 2014
Publication date	Feb 5, 2019
Grant date	Feb 5, 2019

Abstract

An ejector comprises a primary nozzle having an annular wall forming part of an outer boundary of an exhaust portion of a primary flow path of a gas turbine engine. The annular wall has a downstream end defining a plurality of circumferentially distributed lobes. The ejector further comprises a secondary nozzle having an annular wall disposed about the primary nozzle, the primary nozzle and the secondary nozzle defining a secondary flow passage therebetween for channeling a secondary flow. The secondary nozzle defines a mixing zone downstream of an exit of the primary nozzle. A flow guide ring is mounted to the primary nozzle lobes. The ring has an aerodynamic surface extending from a leading edge to a trailing edge respectively disposed upstream and downstream of the exit of the primary nozzle. The aerodynamic surface of the ring is oriented to guide the high velocity primary flow into the mixing zone.

First claim

The invention claimed is:

1. An exhaust section of a turboprop or turboshaft gas turbine engine of the type having a main axis and a primary flow passage channelling a high velocity primary flow, the exhaust section comprising an engine center body having an outer surface forming part of an inner wall of the primary flow passage, the engine center body having a sudden truncation; and an ejector concentrically disposed about the engine center body, the ejector including:
a primary nozzle having an annular wall forming part of an outer boundary of an exhaust portion of the primary flow passage, the annular wall having a downstream end defining a plurality of circumferentially distributed radially inner lobes and having a trailing edge disposed downstream of the engine center body;
a secondary nozzle having an annular wall disposed about the primary nozzle, the primary nozzle and the secondary nozzle defining a secondary flow passage therebetween for channeling a secondary flow, the secondary nozzle defining a mixing zone downstream of an exit of the primary nozzle where the high velocity primary flow and the secondary flow mix together; and
a flow guide ring mounted to the circumferentially distributed radially inner lobes in the exhaust portion of the primary flow passage centrally about the main axis of the engine radially outside and downstream of the engine center body, the flow guide ring having an aerodynamic surface extending from a leading edge to a trailing edge respectively disposed upstream and downstream of the exit of the primary nozzle, the aerodynamic surface being oriented to guide the high velocity primary flow into the mixing zone.

2. The exhaust section according to claim 1 , wherein the aerodynamic surface of the flow guide ring converges radially inwardly towards the main axis in a downstream direction.

3. The exhaust section according to claim 2 , wherein the flow guide ring has a conical shape.

4. The exhaust section according to claim 1 , wherein the flow guide ring extends axially downstream from the exit of the primary nozzle by a distance P 5 , and wherein P 5 is equal to or less than 1 inch.

5. The exhaust section according to claim 2 , wherein the aerodynamic surface of the flow guide ring extends at an angle to the main axis, the angle being equal to or less than 10 degrees.

6. The exhaust section according to claim 5 , wherein the angle is about 5 degrees.

7. The exhaust section according to claim 1 , wherein the lobes have a draft angle comprised between about 0° and about 5°.

8. The exhaust section according to claim 1 , wherein the flow guide ring has an axial length P 2 comprised between about 0.5 inches and about 2 inches.

9. The exhaust section according to claim 1 , wherein each of the circumferentially distributed radially inner lobes has a pair of sidewalls with a bight forming an arcuate trough, and wherein the flow guide ring is directly mounted to a radially inner surface of the arcuate trough of each of the circumferentially distributed radially inner lobes.

Assignees

• Pratt & Whitney Canada

Inventors

• Yan Guorong
• Cunningham Mark
• Di Paola Franco

Classifications

• F02K1/386 Primary

  mixing devices in the jet pipe, e.g. for mixing primary and secondary flow · CPC title

• F05D2220/324

  to drive unshrouded, low solidity propeller · CPC title

• F02C3/10

  with another turbine driving an output shaft but not driving the compressor · CPC title

• F05D2250/232

  conical · CPC title

• F02K1/48

  Corrugated nozzles · CPC title