Auxiliary device for three air flow path gas turbine engine

Patent metadata

Field	Value
Publication number	US-2020102913-A1
Application number	US-201916521970-A
Country	US
Kind code	A1
Filing date	Jul 25, 2019
Priority date	Sep 20, 2013
Publication date	Apr 2, 2020
Grant date	—

Abstract

A gas turbine engine has a fan rotor including at least one stage, with the at least one stage delivering a portion of air into a low pressure duct, and another portion of air into a compressor. The compressor is driven by a turbine rotor, and the fan rotor is driven by a fan drive turbine. A channel selectively communicates air from the low pressure duct across a boost compressor.

First claim

1 . A gas turbine engine comprising:
a fan rotor including at least one stage, with said at least one stage delivering a portion of air into a low pressure duct, and another portion of air into a compressor, said compressor being driven by a turbine rotor, and said fan rotor being driven by a fan drive turbine; a channel selectively communicating air from said low pressure duct across a boost compressor; and wherein the fan rotor includes at least two stages, with an upstream fan stage delivering a portion of air into said low pressure duct, and another portion across a downstream fan stage, air passed downstream of said downstream fan stage being delivered into said compressor and into a bypass duct.

2 . The gas turbine engine as set forth in claim 1 , wherein said fan rotor driving at least three stages, with the first stage fan being said upstream fan stage, and a third stage fan being said downstream fan stage, and there being a second stage fan intermediate said first and said third stage fan.

3 . The gas turbine engine as set forth in claim 1 , wherein said low pressure duct is a bypass duct.

4 . The gas turbine engine as set forth in claim 1 , wherein air downstream of said boost compressor is utilized as cooling air.

5 . The gas turbine engine as set forth in claim 1 , wherein air downstream of said boost compressor is delivered into an exhaust gas downstream of said fan drive turbine.

6 . The gas turbine engine as set forth in claim 5 , wherein an augmentor section is positioned adjacent an exhaust nozzle and air from said boost compressor being directed towards said augmentor section.

7 . The gas turbine engine as set forth in claim 1 , wherein an exit cone positioned downstream of said boost compressor is movable to change a downstream flow cross-sectional area for said boost compressor.

8 . The gas turbine engine as set forth in claim 7 , wherein air downstream of said boost compressor is delivered into an exhaust gas flow downstream of said fan drive turbine.

9 . A gas turbine engine comprising:
a fan rotor including at least one stage, with said at least one stage delivering a portion of air into a low pressure duct, and another portion of air into a compressor, said compressor being driven by a turbine rotor, and said fan rotor being driven by a fan drive turbine; a channel selectively communicating air from said low pressure duct across a boost compressor; and a valve selectively blocks or allows flow through said low pressure duct to an outlet, and when the valve is blocking flow more air is moved into said channel and across the boost compressor.

10 . The gas turbine engine as set forth in claim 9 , wherein said boost compressor is driven by said fan drive turbine.

11 . The gas turbine engine as set forth in claim 10 , wherein a gear box is positioned between said fan drive turbine and said boost compressor, with said gear box affecting a speed change between said fan drive turbine and said boost compressor.

12 . The gas turbine engine as set forth in claim 11 , wherein a connection between said gear box and said boost compressor is a flexible connection.

13 . The gas turbine engine as set forth in claim 9 , wherein a clutch selectively connects or disconnects drive to said boost compressor.

14 . The gas turbine engine as set forth in claim 13 , wherein said clutch is moved to connect drive to said boost compressor when said valve blocks flow through said low pressure duct to said outlet, and said clutch disconnects drive to said boost compressor when said valve allows flow from said low pressure duct to said outlet.

15 . The gas turbine engine as set forth in claim 9 , wherein an exhaust cone positioned downstream of said boost compressor is movable to change a flow cross-sectional area downstream of said boost compressor.

16 . The gas turbine engine as set forth in claim 9 , wherein said channel passes through a turbine exhaust case strut.

17 . The gas turbine engine as set forth in claim 16 , wherein a clutch selectively connects or disconnects drive from said fan drive turbine to said boost compressor.

18 . The gas turbine engine as set forth in claim 9 , wherein a gear box is positioned between said fan drive turbine and said boost compressor, with said gear box affecting a speed change between said fan drive turbine and said boost compressor.

19 . The gas turbine engine as set forth in claim 18 , wherein a clutch selectively connects or disconnects drive from said gear box to said boost compressor.

20 . A gas turbine engine comprising:
a fan rotor including at least one stage, with said at least one stage delivering a portion of air into a low pressure duct, and another portion of air into a compressor, said compressor being driven by a turbine rotor, and said fan rotor being driven by a fan drive turbine; a channel selectively communicating air from said low pressure duct across a boost compressor; wherein air downstream of said boost compressor is delivered into an exhaust gas flow downstream of said fan drive turbine; a valve selectively blocks or allows flow through said low pressure duct to an outlet, and when the valve is blocking flow more air is moved into said channel and across the boost compressor; wherein a clutch selectively connects or disconnects drive to said boost compressor; and wherein said clutch is moved to connect drive to said boost compressor when said valve blocks flow through said low pressure duct to said outlet, and said clutch disconnects drive to said boost compressor when said valve allows flow from said low pressure duct to said outlet.

Assignees

• United Technologies Corp

Inventors

• Roberge Gary D

Classifications

• F02C9/18

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

• F02K3/10

  by after-burners (F02K3/105 takes precedence) · CPC title

• F02K3/077

  the plant being of the multiple flow type, i.e. having three or more flows · CPC title

• F02K3/075 Primary

  controlling flow ratio between flows · CPC title

• 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