Gas turbine engine with stacked accessory components

Patent metadata

Field	Value
Publication number	US-9816441-B2
Application number	US-41363409-A
Country	US
Kind code	B2
Filing date	Mar 30, 2009
Priority date	Mar 30, 2009
Publication date	Nov 14, 2017
Grant date	Nov 14, 2017

Abstract

An engine accessory system for a gas turbine engine includes a first accessory component defined along an accessory axis and a second accessory component mounted to the first accessory component along the accessory axis.

First claim

What is claimed is:

1. An engine accessory system for a gas turbine engine comprising:
a nacelle assembly comprising a core nacelle that surrounds a core engine and a fan nacelle that at least partially surrounds said core nacelle;
a fan case surrounded by said fan nacelle, said fan case defining a fan case outermost diameter;
an intermediate case mounted between said fan case and a high pressure compressor case, said intermediate case defined by an outermost diameter that is less than said fan case outermost diameter at an aft end of said fan case;
an accessory gearbox case section formed as part of said intermediate case and configured to be positioned within said core nacelle, the accessory gearbox including a geartrain;
a first accessory component defined along an accessory axis; and
a second accessory component mounted to said first accessory component along said accessory axis, said first and second accessory components mounted to said accessory gearbox case section and driven by said geartrain.

2. The engine accessory system as recited in claim 1 , wherein said accessory axis is parallel to a gas turbine engine axis of rotation.

3. The engine accessory system as recited in claim 1 , further comprising a transfer gearbox between said second accessory component and said first accessory component.

4. The engine accessory system as recited in claim 1 , further comprising a transfer gearbox between said second accessory component and said first accessory component, said second accessory component driven by said transfer gearbox.

5. The engine accessory system as recited in claim 1 , further comprising a driveshaft parallel to said accessory axis to drive at least said second accessory component.

6. The engine accessory system as recited in claim 5 , further comprising an accessory gearbox driven by the gas turbine engine, said driveshaft driven by said accessory gearbox.

7. The engine accessory system as recited in claim 5 , wherein said driveshaft is concentric with a driveshaft that drives said first accessory component.

8. The engine accessory system as recited in claim 1 , further comprising a driveshaft parallel to said accessory axis to drive said first accessory component and said second accessory component.

9. A gas turbine engine comprising:
a fan case section defined about an engine axis, said fan case section including a fan nacelle surrounding a fan case defined by a fan case outermost diameter;
a core case section attached to said fan case section, said core case section defined about said axis, said core case section including a core nacelle surrounding a core engine, and wherein said fan case section at least partially surrounds said core nacelle;
an intermediate case mounted between said fan case and a high pressure compressor case, said intermediate case defined by an outermost diameter that is less than said fan case outermost diameter at an aft end of said fan case;
an accessory gearbox case section formed as part of said intermediate case and mounted within said core nacelle;
a geartrain within said accessory gearbox case section;
a first accessory component mounted to said accessory gearbox case section along an accessory axis generally parallel to said engine axis, said first accessory component driven by said geartrain; and
a second accessory component mounted to said first accessory component along said accessory axis.

10. The gas turbine engine as recited in claim 9 , further comprising a multiple of fan exit guide vanes mounted to said fan case section and said core case section, said accessory gearbox case section aft of said multiple of fan exit guide vanes.

11. The gas turbine engine as recited in claim 9 , wherein said at least one accessory component is mounted at least partially within a diameter defined by said intermediate case core section.

12. The gas turbine engine as recited in claim 9 , further comprising a transfer gearbox between said second accessory component and said first accessory component, said second accessory component driven by said transfer gearbox.

13. The gas turbine engine as recited in claim 9 , further comprising a driveshaft parallel to said accessory axis to drive at least said second accessory component.

14. The gas turbine engine as recited in claim 9 , further comprising at least first and second tower shafts configured to drive said geartrain.

15. The gas turbine engine as recited in claim 14 , wherein said first and second tower shafts are non-concentric.

16. The gas turbine engine as recited in claim 15 , wherein said first tower shaft extends radially outwardly from said engine axis at a first location and said second tower shaft extends radially outwardly from said engine axis at a second location circumferentially spaced from said first location.

17. The gas turbine engine as recited in claim 14 , further comprising a low speed shaft coupled to a low pressure compressor and a low pressure turbine and a high speed shaft coupled to a high pressure compressor and high pressure turbine, and wherein said first and second tower shafts are driven by said high speed shaft.

18. The gas turbine engine as recited in claim 9 , further comprising a third accessory component mounted to said second accessory component along said accessory axis.

19. The gas turbine engine as recited in claim 18 , further comprising a first drive shaft driven by said geartrain and configured to drive said first accessory component, a second drive shaft configured to drive said second accessory component, and a third drive shaft configured to drive said third accessory component, and wherein said first, second and third drive shafts are concentric with each other.

20. The gas turbine engine as recited in claim 9 , wherein said accessory gear box case section is integrally formed with said intermediate case.

21. The engine accessory system as recited in claim 1 , further comprising at least first and second tower shafts positioned within said accessory gearbox case section and configured to drive said geartrain.

22. The engine accessory system as recited in claim 21 , wherein said first and second tower shafts are non-concentric.

23. The engine accessory system as recited in claim 22 , wherein said first tower shaft extends radially outwardly from a central engine axis at a first location and said second tower shaft extends radially outwardly from said engine axis at a second location circumferentially spaced from said first location.

24. The engine accessory system as recited in claim 1 , further comprising a third accessory component mounted to said second accessory component along said accessory axis.

25. The engine accessory system as recited in claim 24 , further comprising a first drive shaft driven by said geartrain and configured to drive said first accessory component, a second drive shaft configured to drive said second accessory component, and a third drive shaft configured to drive said third accessory component, and wherein said first, second and third drive shafts are concentric with each other.

26. The engine accessory system as recited in claim 1 , wherein said accessory gear box case section is integrally formed with said intermediate case.

27. The engine accessory system as recited in claim 1 , wherein said core nacelle surrounds and encloses said accessory gearbox case section.

28. The engine accessor

Assignees

• Cass Michael F
• Elder James S
• Merry Brian D
• Suciu Gabriel L
• Dye Christopher M
• United Technologies Corp

Inventors

• Cass Michael F
• Elder James S
• Merry Brian D
• Suciu Gabriel L
• Dye Christopher M

Classifications

• F02C7/32 Primary

  Arrangement, mounting, or driving, of auxiliaries · CPC title

• Y02T50/671

  Cross-Sectional Technologies · mapped topic

• Y02T50/60

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