Gas turbine engine with axial movable fan variable area nozzle

Patent metadata

Field	Value
Publication number	US-9771893-B2
Application number	US-201615360092-A
Country	US
Kind code	B2
Filing date	Nov 23, 2016
Priority date	Aug 23, 2007
Publication date	Sep 26, 2017
Grant date	Sep 26, 2017

Abstract

A turbofan engine includes a fan variable area nozzle includes having a first fan nacelle section and a second fan nacelle section movably mounted relative the first fan nacelle section. The second fan nacelle section axially slides afterward relative to the fixed first fan nacelle section to change the effective area of the fan nozzle exit area.

First claim

What is claimed is:

1. A method of designing a turbofan engine comprising:
providing a fan section including a plurality of fan blades, the plurality of fan blades having a design angle of incidence;
providing a low pressure turbine driving the plurality of fan blades through a gear train, the low pressure turbine having a pressure ratio greater than 5:1, and the gear train having a gear reduction ratio of greater than 2.5:1;
providing a fan nacelle and a core nacelle, the fan nacelle at least partially surrounding the core nacelle;
providing a fan bypass flow path defined between the core nacelle and the fan nacelle, and a bypass ratio greater than 10:1;
providing a fan variable area nozzle in communication with the fan bypass flow path and defining a fan nozzle exit area between the fan nacelle and the core nacelle;
providing a duct defined between the fan nacelle and the core nacelle forward of the fan variable area nozzle, the duct having a duct maximum area, and wherein the duct maximum area is greater than the fan nozzle exit area with the fan variable area nozzle in a fully open position;
causing the fan variable area nozzle to vary the fan nozzle exit area to adjust fan bypass air flow in the fan bypass flow path in a plurality of flight conditions such that an angle of incidence on the plurality of fan blades in the plurality of flight conditions is maintained close to the design angle of incidence of the plurality of fan blades;
causing the fan variable nozzle to decrease the fan nozzle exit area for a cruise operating condition; and
causing the fan variable nozzle to increase the fan nozzle exit area for a landing operation condition.

2. The method as recited in claim 1 , wherein the fan variable area nozzle includes a plurality of sectors, and each of the plurality of sectors are simultaneously moveable.

3. The method as recited in claim 2 , further comprising providing a two stage high pressure turbine, and wherein the gear train includes a planetary gear system.

4. The method as recited in claim 3 , further comprising providing a low spool including a low pressure compressor and the low pressure turbine, the low spool driving the low pressure compressor and the planetary gear system.

5. The method as recited in claim 4 , wherein the low pressure turbine is a three stage low pressure turbine.

6. The method as recited in claim 1 , wherein the plurality of fan blades include a fixed stagger angle.

7. The method as recited in claim 6 , further comprising providing a controller to control the fan variable area nozzle to vary the fan nozzle exit area and adjust the bypass ratio, and wherein the controller is an engine controller.

8. The method as recited in claim 1 , wherein the fan variable area nozzle has a maximum required effective area, and the fan nozzle exit area with the fan variable area nozzle in the fully open position is greater than the maximum required effective area of the fan variable area nozzle.

9. The method as recited in claim 1 , wherein the fan variable area nozzle includes a plurality of sectors, and each of the plurality of sectors are simultaneously moveable.

10. The method as recited in claim 1 , wherein the duct has a duct area distribution that is tailored such that the duct maximum area is greater than the fan nozzle exit area with the fan variable area nozzle in the fully open position.

11. The method as recited in claim 1 , wherein the fan variable area nozzle includes a first fan nacelle section, and a second fan nacelle section movably mounted relative the first fan nacelle section and moveable axially relative the first fan nacelle section.

12. The method as recited in claim 11 , further comprising moving the second fan nacelle section along an engine axis of rotation relative to the first fan nacelle section to define an auxiliary port extending between the first fan nacelle section and the second fan nacelle section.

13. The method as recited in claim 12 , wherein the second fan nacelle section defines a trailing edge of the fan variable area nozzle.

14. The method as recited in claim 1 , wherein the fan variable area nozzle has an effective area increase limit, the fan nozzle exit area has a maximum effective area increase, and the fan variable area nozzle achieves the maximum effective area increase of the fan nozzle exit area in operation before the fan variable area nozzle has reached the effective area increase limit.

15. The method as recited in claim 14 , wherein the duct has a duct area distribution and outer wall curvature that is tailored such that the maximum effective area increase of the fan nozzle exit area is achieved in operation before the fan variable area nozzle has reached the effective area increase limit.

16. The method as recited in claim 14 , wherein the fan variable area nozzle includes a plurality of sectors, and each of the plurality of sectors are simultaneously movable.

17. A method of designing a turbofan engine comprising:
providing a fan section including a plurality of fan blades, the plurality of fan blades having a design angle of incidence;
providing a low pressure turbine having a pressure ratio greater than 5:1;
driving the plurality of fan blades through a gear train, the gear train including a planetary gear system having a gear reduction ratio of greater than 2.5:1;
providing a fan nacelle and a core nacelle, the fan nacelle at least partially surrounding the core nacelle;
providing a fan bypass flow path defined between the core nacelle and the fan nacelle, and a bypass ratio greater than 10:1;
providing a fan variable area nozzle in communication with a controller and with the fan bypass flow path, and defining a fan nozzle exit area between the fan nacelle and the core nacelle;
providing a duct defined between the fan nacelle and the core nacelle forward of the fan variable area nozzle, the duct having a duct maximum area, wherein the duct maximum area is greater than the fan nozzle exit area with the fan variable area nozzle in a fully open position;
causing the fan variable area nozzle to vary the fan nozzle exit area in response to the controller in a plurality of flight conditions such that the engine changes to a more favorable fan operating line and avoids an instability region of the fan section;
causing the fan variable area nozzle to decrease the fan nozzle exit area for a cruise operating condition; and
causing the fan variable area nozzle to increase the fan nozzle exit area for a landing operation condition.

18. The method as recited in claim 17 , wherein the fan variable area nozzle includes a plurality of sectors, and each of the plurality of sectors are simultaneously moveable.

19. The method as recited in claim 18 , further comprising providing a low spool including a low pressure compressor and the low pressure turbine, the low spool driving the low pressure compressor and the planetary gear system, and wherein the plurality of fan blades include a fixed stagger angle.

20. The method as recited in claim 19 , further comprising causing the fan variable area nozzle to vary the fan nozzle exit area to adjust fan bypass air flow in the fan bypass flow path in response to the controller in the plurality of flight conditions such that an angle of incidence of the plurality of fan blades in the plurality of flight conditions is maintained close to the design angle of incidence of the plurality of fan blades.

21. The method as recited in claim 17 , wherein the fan variable area nozzle has

Assignees

• United Technologies Corp

Inventors

• Kohlenberg Gregory A
• Zamora Sean P

Classifications

• F02K1/18 Primary

  automatic · CPC title

• B64D31/00

  Power plant control systems; Arrangement of power plant control systems in aircraft · CPC title

• B64D33/04 Primary

  of exhaust outlets or jet pipes · CPC title

• F02C7/36

  Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user ({F02C3/107 - F02C3/13 and} F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H) · CPC title

• F05D2220/323

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