Gas turbine engine and method of assembling the same

Patent metadata

Field	Value
Publication number	US-10113508-B2
Application number	US-201514940543-A
Country	US
Kind code	B2
Filing date	Nov 13, 2015
Priority date	Nov 21, 2014
Publication date	Oct 30, 2018
Grant date	Oct 30, 2018

Abstract

A gas turbine engine having a centerline axis is provided. The gas turbine engine includes a fan and a fan cowl assembly surrounding the fan to define a bypass duct configured to channel airflow for the fan. The fan cowl assembly includes a stationary cowl and a transcowl. The gas turbine engine further includes a plurality of actuators configured for displacing the transcowl relative to the stationary cowl. Each of the actuators is skewed relative to the centerline axis of the engine.

First claim

What is claimed is:

1. A gas turbine engine having a centerline axis, said gas turbine engine comprising:
a variable pitch fan configured for generating reverse thrust;
a fan cowl assembly surrounding said fan to define a bypass duct configured to channel airflow for said fan, wherein said fan cowl assembly comprises a stationary cowl and a transcowl; and
a plurality of actuators are circumferentially spaced apart from one another, alternatingly skewed in different directions relative to the centerline axis of the engine and configured for displacing said transcowl relative to said stationary cowl to form an auxiliary inlet into said bypass duct when said fan is generating reverse thrust.

2. A gas turbine engine in accordance with claim 1 , wherein said plurality of actuators comprises at least six of said actuators.

3. A gas turbine engine in accordance with claim 1 , wherein said actuators are pivotable.

4. A gas turbine engine in accordance with claim 3 , wherein said actuators are pivotable while displacing said transcowl.

5. A gas turbine engine in accordance with claim 1 , wherein said transcowl comprises a front edge having a cutout, and wherein said stationary cowl comprises a key sized for insertion into said cutout.

6. A gas turbine engine in accordance with claim 1 , further comprising a core having a core cowl, wherein said core cowl comprises a pair of substantially semi-annular doors that are openable away from one another.

7. A gas turbine engine in accordance with claim 1 , further comprising a hydraulic system configured for operating said actuators, said hydraulic system comprising a supply conduit for delivering hydraulic fluid to each of said actuators and a flow limiting member at a junction of said conduit and its associated actuator, wherein each flow limiting member comprises a plate and an orifice defined in said plate, said orifice being smaller than said conduit.

8. A method of assembling a gas turbine engine having a centerline axis, said method comprising:
providing a fan;
surrounding the fan with a fan cowl assembly to define a bypass duct configured to channel airflow for the fan, wherein the fan cowl assembly includes a stationary cowl and a transcowl; and
coupling the transcowl to the stationary cowl via a plurality of actuators configured for displacing the transcowl relative to the stationary cowl, wherein the actuators are alternatingly skewed in different directions relative to the centerline axis of the engine and
further comprising circumferentially spacing the actuators apart from one another.

9. A method in accordance with claim 8 , further comprising providing the fan as a variable pitch fan configured for generating reverse thrust.

10. A method in accordance with claim 9 , further comprising connecting the actuators to the stationary cowl and the transcowl such that the actuators are configured for spacing the transcowl from the stationary cowl to form an auxiliary inlet into the bypass duct when the fan is generating reverse thrust.

11. A method in accordance with claim 8 , further comprising coupling the transcowl to the stationary cowl via at least six actuators.

12. A method in accordance with claim 8 , further comprising pivotably coupling the actuators to the stationary cowl and the transcowl.

13. A gas turbine engine having a centerline axis, said gas turbine engine comprising:
a variable pitch fan;
a fan cowl assembly surrounding said fan to define a bypass duct configured to channel airflow for said fan, wherein said fan cowl assembly comprises a stationary cowl and a transcowl;
at least six actuators coupling said stationary cowl to said transcowl such that said transcowl is displaceable relative to said stationary cowl via said actuators to define an auxiliary inlet for airflow into said bypass duct,
wherein said actuators are circumferentially spaced apart from one another and are alternatingly skewed relative to the centerline axis so as to be triangulated.

Assignees

• Gen Electric

Inventors

• Stuart Alan Roy
• Lonneman Patrick John

Classifications

• F05D2250/314

  the axes being inclined in relation to each other · CPC title

• F04D19/002

  Axial flow fans · CPC title

• F04D27/002

  by varying geometry within the pumps, e.g. by adjusting vanes · CPC title

• F05D2250/34

  translated · CPC title

• F02K1/72 Primary

  the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow · CPC title