Engine bypass valve

Patent metadata

Field	Value
Publication number	US-2016298550-A1
Application number	US-201514685166-A
Country	US
Kind code	A1
Filing date	Apr 13, 2015
Priority date	Apr 13, 2015
Publication date	Oct 13, 2016
Grant date	—

Abstract

Aspects of the disclosure are directed to an engine of an aircraft. The engine may include a first fan configured to output a first air flow, a second fan configured to receive a first portion of the first air flow and output a second air flow, a core configured to receive a first portion of the second air flow and generate a first stream, and at least one valve configured to assume one of at least three states in association with a generation of a second stream and a third stream based on at least one of the first air flow and the second air flow.

First claim

What is claimed is:

1 . An engine of an aircraft, comprising:
a first fan configured to output a first air flow; a second fan configured to receive a first portion of the first air flow and output a second air flow; a core configured to receive a first portion of the second air flow and generate a first stream; and at least one valve configured to assume one of at least three states in association with a generation of a second stream and a third stream based on at least one of the first air flow and the second air flow.

2 . The engine of claim 1 , wherein when the at least one valve is in a first of the at least three states the second stream and the third stream are generated based on a second portion of the second air flow.

3 . The engine of claim 2 , wherein when the at least one valve is in a second of the at least three states the second stream is generated based on the second portion of the second air flow and the third stream is generated based on a second portion of the first air flow.

4 . The engine of claim 3 , wherein when the at least one valve is in a third of the at least three states the second stream is generated based on a mixture of the second portion of the first air flow and the second portion of the second air flow.

5 . The engine of claim 4 , wherein when the at least one valve is in the third of the at least three states the third stream is generated based on the second portion of the first air flow.

6 . The engine of claim 3 , wherein the second portion of the first air flow bypasses the second fan.

7 . The engine of claim 1 , further comprising:
a heat exchanger, wherein the third stream is based on an output of the heat exchanger.

8 . The engine of claim 1 , wherein the first fan includes a plurality of stages.

9 . The engine of claim 1 , wherein the core includes a turbine arranged as a plurality of sections, and wherein a first of the turbine sections is configured to drive the first fan, and wherein a second of the turbine sections is configured to drive the second fan.

10 . The engine of claim 1 , wherein the first fan is located forward of the second fan with respect to an inlet air flow received by the first fan, and wherein the second fan is located forward of the core with respect to the inlet air flow.

11 . The engine of claim 1 , further comprising:
a nozzle configured to output a mixture of the first and a portion of the second stream.

12 . The engine of claim 1 , further comprising:
at least one nozzle configured to output at least the third stream.

13 . The engine of claim 1 , further comprising:
a duct located radially outboard of the third stream.

14 . The engine of claim 13 , wherein the duct is configured to convey a second portion of the second air flow when the at least one valve is in a first of the at least three states.

15 . The engine of claim 14 , wherein the duct is configured to convey a second portion of the first air flow when the at least one valve is in a second of the at least three states.

16 . The engine of claim 15 , wherein the duct is configured to convey the second portion of the second air flow when the at least one valve is in a third of the at least three states.

17 . The engine of claim 1 , wherein the third stream is discontinuous in nature in the engine forward-to-aft, and wherein the at least one valve includes a plurality of valves, and wherein a first of the valves is located at a first location and a second of the valves is located at a second location, and wherein the first and second locations are substantially symmetrical with respect to an axial centerline of the engine.

18 . An engine of an aircraft, comprising:
a first fan configured to output a first air flow; a second fan configured to receive a first portion of the first air flow and output a second air flow; a core configured to receive a first portion of the second air flow and generate a first stream; and at least one valve configured to assume one of at least three states in association with a generation of a second stream and a third stream, wherein the second stream is based on a second portion of the second air flow.

19 . The engine of claim 18 , wherein the second fan comprises a first inducer stage and a second inducer stage.

20 . The engine of claim 19 , wherein the first inducer stage comprises a first set of vanes and a first set of blades, and wherein the second inducer stages comprises a second set of vanes and a second set of blades, and wherein the first set of vanes and the second set of vanes are part of a core stator structure, and wherein the first set of blades and the second set of blades are part of at least one rotor.

Assignees

• United Technologies Corp

Inventors

• Kupratis Daniel B
• Hanlon Christopher J
• Ledwith Jr Walter A

Classifications

• F02C3/13

  having variable working fluid interconnections between turbines or compressors or stages of different rotors {(controlling flow ratio between different flows of multi-flow jet-propulsion plant, e.g. ducted fan F02K3/075)} · CPC title

• F02C9/18 Primary

  by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)} · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F05D2260/213

  by the provision of a heat exchanger within the cooling circuit · CPC title