Turbine engine with access door to engine core

Patent metadata

Field	Value
Publication number	US-9255547-B2
Application number	US-201213536038-A
Country	US
Kind code	B2
Filing date	Jun 28, 2012
Priority date	Aug 25, 2011
Publication date	Feb 9, 2016
Grant date	Feb 9, 2016

Abstract

A turbine engine includes an engine core bounded by a bypass duct, a first portion of the bypass duct defined by a fan casing having a radially inner wall and a radially outer wall, a second portion of the bypass duct defined by a radially inner wall and a radially outer wall, a third portion of the bypass duct provided as at least one access door comprising a flow guide structure; and a thrust reverser mechanism coupled to the fan casing.

First claim

The invention claimed is:

1. A turbine engine comprising:
an engine core bounded by a bypass duct;
a first portion of the bypass duct defined by a fan casing having a first radially inner wall and a first radially outer wall;
a second portion of the bypass duct defined by a second radially inner wall and a second radially outer wall;
a third portion of the bypass duct provided as at least one access door comprising a flow guide structure; and
a thrust reverser mechanism coupled to the fan casing, wherein
the at least one access door is pivotable between an open position and a closed position relative to the thrust reverser mechanism;
the second radially outer wall is a separate component to the access door and remains in place around the engine core when the access door is opened;
the flow guide structure has a first panel spaced apart from a second panel such that in the closed position the first panel forms a continuous flow surface with the second radially outer wall and the second panel forms a continuous flow surface with the second radially inner wall and covers a section of the engine core;
in the open position, the access door provides access to the engine core; and
when the access door is in the open position and the second radially inner wall is open, the second radially inner wall provides access to the engine core.

2. The turbine engine as claimed in claim 1 , wherein the thrust reverser mechanism is provided upstream of the flow guide structure.

3. The turbine engine as claimed in claim 2 , wherein, in the closed position, a section of an outer wall of the access door extends upstream from the flow guide structure and bounds at least part of the thrust reverser mechanism, such that when the access door is in the open position the access door provides access to the at least part of the thrust reverser mechanism.

4. The turbine engine as claimed in claim 3 , wherein the thrust reverser mechanism comprises a flow turning device, and the access door outer wall bounds the flow turning device when in the closed position and provides access to the flow turning device when in the open position.

5. The turbine engine as claimed in claim 3 , wherein the thrust reverser mechanism comprises an actuation rod for displacement of the third portion relative to the first portion, and the access door outer wall bounds the actuation rod when in the closed position and provides access to the actuation rod when in the open position.

6. The turbine engine as claimed in claim 1 , wherein the access door is arcuate.

7. The turbine engine as claimed in claim 1 , wherein the at least one access door comprises at least two access doors, each of the at least two access doors being arcuate and pivotably mounted.

8. The turbine engine as claimed in claim 7 , wherein the at least two access doors bound a complete circumference of the engine core.

9. The turbine engine as claimed in claim 1 , wherein the thrust reverser mechanism has a blocker door with a first end pivotably mounted to the second radially outer wall and a second end coupled to the first radially inner wall or the second radially inner wall via a link member.

10. The turbine engine as claimed in claim 1 , wherein the second radially inner wall is pivotably coupled to the fan casing such that when the second radially inner wall is closed the second radially inner wall forms a continuous flow surface with the first radially inner wall and when open provides access to the engine core.

11. The turbine engine as claimed in claim 1 , wherein the second radially inner wall comprises a first section located upstream of a second section, the first section and the second section being connected by a hinge.

12. The turbine engine as claimed in claim 9 , wherein the link member is hinged at a point along a length of the link member.

13. The turbine engine as claimed in claim 1 , wherein the first portion of the bypass duct is upstream of the second portion of the bypass duct, and the second portion of the bypass duct is upstream of the third portion of the bypass duct.

14. The turbine engine as claimed in claim 1 , further comprising a plurality of blocker doors.

Assignees

• Beardsley Peter
• Rolls Royce Plc

Inventors

• Beardsley Peter

Classifications

• F05D2260/02

  Transport and handling during maintenance and repair · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · 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

• F05D2230/72

  Maintenance · CPC title

• B64D29/06

  Attaching of nacelles, fairings or cowlings · CPC title