ACCESS DOOR FOR GAS TURBINE ENGINE COMPONENTS

• US 20090129922A1
• Filed: 05/30/2007
• Published: 05/21/2009
• Est. Priority Date: 05/30/2007
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Cloft, Thomas G., Gukeisen, Robert L.
• Granted Patent: US 9,126,691 B2
• Time in Patent Office: Days
• US Class Current: 415/213.100
• CPC Class Codes: B64D 29/08 Inspection panels for power plants
• CPC Class Codes: F01D 25/24 Casings modified for heating or cooling F01D25/14; Casing parts, e.g. diaphragms, casing fastenings casings for rotary machines or engines in general F16M ; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045
• CPC Class Codes: F02K 3/06 with front fan
• CPC Class Codes: F05D 2240/14 Casings or housings protecting or supporting assemblies within
• CPC Class Codes: F05D 2240/90 Mounting on supporting structures or systems
• CPC Class Codes: F05D 2250/30 Arrangement of components

Abstract

An access door is provided in a housing for a gas turbine engine, with the access door being movable to an access position independent of any required movement of any cowl door or a fan duct door.

Claims

1. A nacelle for a gas turbine engine comprising:

a nacelle housing surrounding a central axis;

a pivotable door as part of said nacelle housing, said pivotable door defining an inner housing for surrounding internal components of a gas turbine engine, said inner housing being pivotable as part of said pivotable door; and

an access door being movable independent of said pivotable door to provide access to components within said inner housing.

2. The nacelle as set forth in claim 1, wherein said access door is also movable with said pivotable door.

3. The nacelle as set forth in claim 2, wherein said access door is pivotable relative to said pivotable door.

4. The nacelle as set forth in claim 3, wherein said pivotable door is at least two fan duct doors each independently pivotable about an axis parallel to said central axis, and each of said at least two fan duct doors carrying an access door which is pivotable relative to said fan duct door.

5. The nacelle as set forth in claim 4, wherein said access doors pivot about an axis which is parallel to said central axis.

6. The nacelle as set forth in claim 1, wherein said access door pivots about an axis which is perpendicular to an axis that is parallel to said central axis.

7. A gas turbine engine comprising:

a fan, and a central core downstream of said fan, an inner housing surrounding said central core;

a nacelle surrounding said inner housing, at least a portion of said inner housing and said nacelle being provided by a pivotable door to provide access to an interior of said inner housing;

auxiliary components positioned within said inner housing; and

an access door for providing access to said auxiliary components without requiring said pivotable door to be opened.

8. The gas turbine engine as set forth in claim 7, wherein said access door is also movable with said pivotable door.

9. The gas turbine engine as set forth in claim 8, wherein said access door is pivotable relative to said pivotable door.

10. The gas turbine engine as set forth in claim 9, wherein said pivotable door includes at least two fan duct doors each independently pivotable about an axis parallel to said central axis, and each of said at least two fan duct doors carrying an access door which is pivotable relative to said fan duct door.

11. The gas turbine engine as set forth in claim 10, wherein said access doors pivot about an axis which is parallel to said central axis.

12. The gas turbine engine as set forth in claim 7, wherein said access door pivots about an axis which is perpendicular to an axis parallel to said central axis.

13. The gas turbine engine as set forth in claim 7, wherein said access door provides an opening sufficiently large to remove at least one of the auxiliary components.

14. The gas turbine engine as set forth in claim 13, wherein said auxiliary components include at least one of an auxiliary gear box and an electrical generator.

15. A method of maintaining a gas turbine engine comprising the steps of:

providing a fan, and a central core downstream of said fan, providing an inner housing surrounding said central core, and providing a nacelle surrounding said inner housing, at least a portion of said nacelle and said inner housing being provided by a pivotable door, said pivotable door being pivotable to provide access to an interior of said inner housing, and auxiliary components positioned within said inner housing; and

providing an access door, moving said access door relative to said pivotable door to provide access to said auxiliary components for maintenance, while said pivotable door remains closed.

16. The method as set forth in claim 15, wherein said access door is pivotable with said pivotable door.

17. The method as set forth in claim 15, wherein said auxiliary component is removed through an opening provided by said access door when said access door is open.

18. The method as set forth in claim 17, wherein the auxiliary components include at least one of an auxiliary gear box and an electrical generator and said at least one of said components being removed through the opening provided when said access door is open.