Auxiliary device for three air flow path gas turbine engine

Patent metadata

Field	Value
Publication number	US-11261827-B2
Application number	US-201916521970-A
Country	US
Kind code	B2
Filing date	Jul 25, 2019
Priority date	Sep 20, 2013
Publication date	Mar 1, 2022
Grant date	Mar 1, 2022

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

The invention claimed is:

1. A gas turbine engine comprising:
a fan rotor delivering a first portion of air into a low pressure duct, and a second portion of air into a compressor, said compressor being driven by a turbine rotor, said fan rotor being driven by a fan drive turbine, and said second portion of air forming a core air flow passing through said compressor, said turbine rotor, and said fan drive turbine;
a channel selectively communicating a first part of said first portion of 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 of the at least two stages delivering said first portion of air into said low pressure duct and a third portion of air across a downstream fan stage of the at least two stages, said third portion of air passed downstream of said downstream fan stage being delivered as said second portion of air into said compressor and as a fourth portion of air into a bypass duct;
the first part of the first portion of air in said channel passing radially inwardly from said low pressure duct to be radially inward of the core air flow downstream of said fan drive turbine, and the first part of the first portion of air downstream of the boost compressor passing outwardly to mix into said core air flow downstream of said fan drive turbine.

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

3. The gas turbine engine as set forth in claim 1 , wherein the first part of the first portion of air downstream of said boost compressor is split into a cooling portion utilized as cooling air, and an exhaust portion exiting into the core air flow.

4. The gas turbine engine as set forth in claim 1 , wherein an augmentor section is positioned adjacent an exhaust nozzle of the gas turbine engine and the first part of the first portion of air downstream from said boost compressor is directed towards said augmentor section.

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

6. The gas turbine engine as set forth in claim 1 , wherein only the first part of the first portion of air in the low pressure duct is communicated into the channel, with the remainder of the first portion of air in the low pressure duct passing downstream within the low pressure duct to an outlet of the low pressure duct.

7. A gas turbine engine comprising:
a fan rotor including at least one stage, with said at least one stage delivering a first portion of air into a low pressure duct, and a second 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 a first part of the first portion of air from said low pressure duct across a boost compressor;
a valve selectively blocks or allows flow through said low pressure duct to an outlet, and when the valve is blocking flow more of the first portion of air is moved into said channel and across the boost compressor as the first part of the first portion of air;
wherein said channel passes radially inward through a turbine exhaust case strut to the boost compressor; and
wherein a clutch selectively connects or disconnects drive from said fan drive turbine to said boost compressor.

8. The gas turbine engine as set forth in claim 7 , wherein said boost compressor is driven by said fan drive turbine.

9. The gas turbine engine as set forth in claim 8 , 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.

10. The gas turbine engine as set forth in claim 9 , wherein a connection between said gear box and said boost compressor is a flexible connection.

11. The gas turbine engine as set forth in claim 7 , wherein a clutch selectively connects or disconnects drive to said boost compressor.

12. The gas turbine engine as set forth in claim 11 , 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.

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

14. The gas turbine engine as set forth in claim 7 , 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.

15. A gas turbine engine comprising:
a fan rotor including at least one stage, with said at least one stage delivering a first portion of air into a low pressure duct, and a second 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 a first part of the first portion of air from said low pressure duct across a boost compressor;
wherein the first part of the first portion of 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 of the first portion of air is moved into said channel and across the boost compressor as the first part of the first portion of air;
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.

16. The gas turbine engine as set forth in claim 15 , wherein said channel passes through a turbine exhaust case strut.

Assignees

• Raytheon Tech Corp

Inventors

• Roberge Gary D

Classifications

• F02K3/00 Primary

  Plants including a gas turbine driving a compressor or a ducted fan · CPC title

• F02C7/18

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title

• F02K3/10

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

• F02K3/11

  by means of burners or combustion chambers · CPC title

• F02K3/075 Primary

  controlling flow ratio between flows · CPC title