Bifurcation fire purge system for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-9482157-B2
Application number	US-201414181829-A
Country	US
Kind code	B2
Filing date	Feb 17, 2014
Priority date	Feb 28, 2013
Publication date	Nov 1, 2016
Grant date	Nov 1, 2016

Abstract

A bifurcation assembly for a gas turbine engine is disclosed and includes a housing defining an inner cavity. A first partition and a second partition extend across the inner cavity and define a buffer area therebetween. Openings through the first and second partitions define passageway for supply conduits. A control device governs the flow of a purge gas into the buffer area for blocking the spread of fire. The purge gas provides a barrier to the spread of fire and heat through the bifurcation assembly.

First claim

What is claimed is:

1. A bifurcation assembly for a gas turbine engine comprising:
a housing defining inner cavity;
a first partition extending across the inner cavity;
a second partition extending across the inner cavity spaced apart from the first partition to define a buffer area therebetween;
at least one opening through the first partition and the second partition defining a passageway for a supply conduit; and
a control device governing the flow of a purge gas into the buffer area blocking the spread of fire through the buffer area.

2. The bifurcation assembly as recited in claim 1 , including a grommet within the opening and in communication with the buffer area for communicating purge gas into the passageway for the supply conduit.

3. The bifurcation assembly as recited in claim 1 , wherein one of the first partition and the second partition include a plurality of openings in communication with the buffer area for communicating purge gas to a side opposite the buffer area.

4. The bifurcation assembly as recited in claim 1 , including a fire retardant material supported within the housing that is activated in response to heat to produce a flame retardant gas.

5. The bifurcation assembly as recited in claim 4 , wherein the fire retardant material is supported on an inner periphery of the housing within the buffer area.

6. The bifurcation assembly as recited in claim 1 , wherein the control device comprises a valve that moves to an open position allowing a flow of purge gas into the buffer area responsive to a temperature detected that is indicative of a fire.

7. The bifurcation assembly as recited in claim 1 , wherein the control device comprises a fixed orifice blocked by a plug that melts responsive to exposure to heat above a defined temperature for communicating the purge gas to the buffer area.

8. A gas turbine engine comprising:
a fan section including a plurality of fan blades rotatable about an axis;
a fan case circumscribing the fan section;
a core engine section including a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, and a geared architecture driven by the turbine section for rotating the fan about the axis;
a bifurcation within a passageway defined between the core engine section and the fan case defining a passageway for supply conduits to the core engine, the bifurcation including; a housing supporting a first partition spaced part from a second partition to define a buffer area therebetween, at least one opening through the first partition and the second partition defining a passageway for a supply conduit, and a control device governing the flow of a purge gas into the buffer area for blocking the spread of fire through the buffer area.

9. The gas turbine engine assembly as recited in claim 8 , including a grommet within the opening in communication with the buffer area for communicating purge gas into the passageway for the supply conduit.

10. The gas turbine engine assembly as recited in claim 8 , including a fire retardant material supported within the housing that is activated in response to heat to produce a flame retardant gas.

11. The gas turbine engine assembly as recited in claim 10 , wherein the control device comprises a valve that moves to an open position allowing a flow of purge gas into the buffer area responsive to a temperature detected indicative of a fire.

12. The gas turbine engine assembly as recited in claim 10 , wherein the control device comprises a fixed orifice blocked by a plug that melts responsive to exposure to heat above a defined temperature for communicating the purge gas to the buffer area.

13. A method of isolating a core engine portion of a gas turbine engine comprising:
defining a plurality passageways for supply conduits through a bifurcation, wherein each of the plurality of passageways extend through partitions extending through a buffer area;
defining a flow path for high pressure purge gas through the buffer area; and
controlling the flow of the high pressure purge gas into the buffer area responsive to detecting a temperature detected that is indicative of fire.

14. The method as recited in claim 13 , including the step of flowing the high pressure purge gas through the buffer area to prevent the spread of fire.

15. The method as recited in claim 13 , wherein one of the partitions includes openings in communication with the buffer area.

16. The method as recited in claim 13 , including supporting a fire retardant material that produces a flame retardant gas responsive to exposure to a temperature above a defined level within the bifurcation.

Assignees

• United Technologies Corp

Inventors

• Nilsson Cody A
• Fowler Robert B

Classifications

• B64D2045/009

  Fire detection or protection; Erosion protection, e.g. from airborne particles · CPC title

• F02C6/08

  the gas being bled from the gas-turbine compressor · CPC title

• F02C7/25 Primary

  Fire protection or prevention (in general A62) · CPC title

• A62C3/08

  in aircraft {(A62C3/0207 takes precedence)} · CPC title