Nacelle bifurcation for gas turbine engine

Patent metadata

Field	Value
Publication number	US-9249731-B2
Application number	US-201213488909-A
Country	US
Kind code	B2
Filing date	Jun 5, 2012
Priority date	Jun 5, 2012
Publication date	Feb 2, 2016
Grant date	Feb 2, 2016

Abstract

A nacelle structure for a gas turbine engine includes a core engine nacelle disposed about an engine axis and an outer nacelle disposed about the core engine nacelle. A bifurcation extends between the outer nacelle and the core engine nacelle along a bifurcation axis extending between the outer nacelle and the core engine nacelle. The bifurcation includes at least one mounting surface that is disposed at a non-normal angle relative to the bifurcation axis.

First claim

The invention claimed is:

1. A nacelle structure for a gas turbine engine comprising:
a core engine nacelle disposed about an engine axis;
an outer nacelle disposed about the core engine nacelle; and
at least one bifurcation extending between the outer nacelle and the core engine nacelle about a bifurcation axis extending between the core engine nacelle and the outer nacelle, the at least one bifurcation including walls defining an inner cavity and including a mounting surface disposed within the inner cavity that extends between the walls and is spaced apart from both the core engine nacelle and the outer nacelle, the mounting surface disposed at a non-normal angle relative to the bifurcation axis.

2. The nacelle structure as recited in claim 1 , including at least one interface conduit extending through the bifurcation to the core engine nacelle and secured to the mounting surface.

3. The nacelle structure as recited in claim 2 , including a bracket secured to the mounting surface for holding the interface conduit.

4. The nacelle structure as recited in claim 3 , wherein the bracket includes a flange for securement to the mounting surface and an extension extending from the flange at a non-normal angle for securing the interface conduit.

5. The nacelle structure as recited in claim 3 , wherein the interface conduit includes a bend portion and a through portion that extends through an opening in the mounting surface and the through portion is disposed normal to the mounting surface.

6. The nacelle structure as recited in claim 1 , wherein the bifurcation includes walls spaced apart from each other defining an interior space with the mounting surface disposed between the walls at the non-normal angle.

7. The nacelle structure as recited in claim 6 , wherein the mounting surface is disposed at an angle relative to an axis parallel with the engine axis.

8. The nacelle structure as recited in claim 6 , wherein the mounting surface is disposed at an angle relative to an axis transverse to the bifurcation axis.

9. The nacelle structure as recited in claim 1 , wherein the mounting surface comprises at least two mounting surfaces each disposed at a different non-normal angle relative to the bifurcation axis.

10. The nacelle structure as recited in claim 1 , wherein the mounting surface comprises at least two mounting surfaces with at least one disposed at the non-normal angle relative to the bifurcation axis.

11. A gas turbine engine comprising:
a fan section including a plurality of fan blades rotatable about an engine axis;
a core engine disposed about the engine axis including a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor;
a core engine nacelle disposed about the core engine;
an outer nacelle disposed about the fan section; and
at least one bifurcation extending between the outer nacelle and the core engine nacelle along a bifurcation axis extending between the outer nacelle and the core engine nacelle , the at least one bifurcation including walls defining an inner cavity and a mounting surface spaced apart from both the core engine nacelle and the outer nacelle and extending across the inner cavity between the walls, the mounting surface disposed at a non-normal angle relative to the bifurcation axis.

12. The gas turbine engine as recited in claim 11 , including a geared architecture driven by the turbine section for rotating the fan about the engine axis.

13. The gas turbine engine as recited in claim 11 , including at least one interface conduit extending through the bifurcation to the core engine nacelle and secured to the mounting surface.

14. The gas turbine engine as recited in claim 13 , including a bracket having a flange for securement of the interface conduit to the mounting surface and an extension extending from the flange at a non-normal angle for securing the interface conduit extending.

15. The gas turbine engine as recited in claim 13 , wherein the interface conduit includes a bend portion and a through portion that extends through an opening in the mounting surface and the through portion is disposed normal to the mounting surface.

16. The gas turbine engine as recited in claim 11 , wherein the mounting surface is disposed at an angle relative to an axis parallel with the engine axis.

17. The gas turbine engine as recited in claim 11 , wherein the mounting surface is disposed at an angle relative to an axis transverse to the bifurcation axis.

18. The nacelle structure as recited in claim 1 , wherein the mounting surface comprises at least two mounting surfaces each disposed at a different non-normal angle relative to the bifurcation axis.

Assignees

• Sidelkovskiy Dmitriy B
• Malecki Robert E
• Petrenko Oleg
• United Technologies Corp

Inventors

• Sidelkovskiy Dmitriy B
• Malecki Robert E
• Petrenko Oleg

Classifications

• F02C7/20 Primary

  Mounting or supporting of plant; Accommodating heat expansion or creep · CPC title

• F02K3/06

  with front fan · CPC title

• F02C7/32

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

• F01D9/065

  Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26) · CPC title