Preloaded AFT vent area for low pressure fan ducts

Patent metadata

Field	Value
Publication number	US-10294863-B2
Application number	US-201414903324-A
Country	US
Kind code	B2
Filing date	Apr 22, 2014
Priority date	Jul 9, 2013
Publication date	May 21, 2019
Grant date	May 21, 2019

Abstract

A core compartment aft vent is disclosed. The core compartment aft vent may include a flexible core engine cowl surrounding a core engine case. A plurality of circumferentially spaced bumpers may be disposed within the aft vent and in operative contact with the flexible core engine cowl.

First claim

What is claimed is:

1. A core compartment aft vent, comprising:
a flexible core engine cowl;
a core engine case, the core engine case surrounded by the flexible core engine cowl; and
an annular bumper, the annular bumper located between the flexible core engine cowl and the core engine case, the annular bumper in operative association with the flexible core engine cowl,
wherein the annular bumper and the flexible core engine cowl are telescopically operatively associated such that the flexible core engine cowl is capable of extending radially outwardly from the annular bumper.

2. The aft vent of claim 1 , wherein the annular bumper and the flexible core engine cowl are telescopically operatively associated through use of slip joints.

3. A core compartment aft vent, comprising:
a flexible core engine cowl;
a core engine case, the core engine case surrounded by the flexible core engine cowl; and
an annular bumper, the annular bumper located between the flexible core engine cowl and the core engine case, the annular bumper in operative association with the flexible core engine cowl,
wherein the aft vent further includes a plurality of circumferentially spaced bumpers, each of the plurality of circumferentially spaced bumpers having one end affixed to the core engine case and another end affixed to the annular bumper.

4. A gas turbine engine, comprising:
a core engine case;
a flexible core engine cowl, the flexible core engine cowl surrounding the core engine case;
a core compartment aft vent, the core compartment aft vent defined between the flexible core engine cowl and the core engine case; and
an annular bumper, the annular bumper located between the flexible core engine cowl and the core engine case, the annular bumper in operative association with the flexible core engine cowl,
wherein the annular bumper and the flexible core engine cowl are telescopically operatively associated such that the flexible core engine cowl is capable of extending radially outwardly from the annular bumper.

5. The gas turbine engine of claim 4 , wherein the annular bumper and the flexible core engine cowl are telescopically operatively associated through use of slip joints.

6. A gas turbine engine, comprising:
a core engine case;
a flexible core engine cowl, the flexible core engine cowl surrounding the core engine case;
a core compartment aft vent, the core compartment aft vent defined between the flexible core engine cowl and the core engine case; and
an annular bumper, the annular bumper located between the flexible core engine cowl and the core engine case, the annular bumper in operative association with the flexible core engine cowl,
wherein the gas turbine engine further includes a plurality of circumferentially spaced bumpers, wherein each of the plurality of circumferentially spaced bumpers include one end affixed to the core engine case and another end affixed to the bumper.

Assignees

• United Technologies Corp

Inventors

• Ronan Michael
• Papa Federico
• Evetts Joseph D

Classifications

• Y02T50/675

  Cross-Sectional Technologies · mapped topic

• F05D2300/121

  Aluminium · CPC title

• F02C7/12

  Cooling of plants (of component parts, see the relevant subclasses, e.g. F01D; cooling of engines in general F01P) · CPC title

• F01D25/26

  Double casings; Measures against temperature strain in casings · CPC title

• F05D2230/232

  by welding · CPC title