Method and system for sealing an annulus

Patent metadata

Field	Value
Publication number	US-9896970-B2
Application number	US-201514928077-A
Country	US
Kind code	B2
Filing date	Oct 30, 2015
Priority date	Nov 14, 2014
Publication date	Feb 20, 2018
Grant date	Feb 20, 2018

Abstract

A method and system for a compartment baffle system are provided. The compartment baffle system includes a first baffle portion extending along an axial length of a casing, the first baffle portion extending radially outwardly from an outer surface of the casing and a second baffle portion extending at least partially radially outwardly from the first baffle portion. The second baffle portion further includes a radially inner edge supported by the first baffle portion and a radially outer edge extending proximate an inner surface of a radially outer cowl. The compartment baffle system also includes a gap extending between the radially outer edge and the inner surface.

First claim

What is claimed is:

1. A compartment baffle system comprising:
a first baffle portion extending along an axial length of a casing, said first baffle portion extending radially outwardly from an outer surface of the casing;
a second baffle portion extending at least partially radially outwardly from said first baffle portion, said second baffle portion comprising:
a radially inner edge supported by said first baffle portion; and
a radially outer edge extending proximate an inner surface of a radially outer cowl; and
a gap extending between said radially outer edge and said inner surface.

2. The compartment baffle system of claim 1 , wherein said casing includes a cylindrical cross-section.

3. The compartment baffle system of claim 1 , wherein said cowl includes a cylindrical cross-section concentric with a longitudinal axis of said casing.

4. The compartment baffle system of claim 1 , wherein said radially inner edge is coupled to a radially outer edge of said first baffle portion.

5. The compartment baffle system of claim 1 , wherein said radially inner edge of said second baffle portion is spaced circumferentially from said radially outer edge of said first baffle portion.

6. The compartment baffle system of claim 1 , further comprising a spacer positioned between said radially inner edge of said second baffle portion and said radially outer edge of said first baffle portion, said spacer configured to maintain a gap between said radially inner edge of said second baffle portion and said radially outer edge of said first baffle portion.

7. The compartment baffle system of claim 1 , further comprising a seal between said cowl and said radially outer edge of said second baffle portion.

8. The compartment baffle system of claim 1 , further comprising at least one of a brush seal and a bulb seal between said cowl and said radially outer edge of said second baffle portion.

9. A gas turbine engine comprising:
a gas generator comprising a shaft having an axis of rotation;
a fan casing at least partially circumscribing said gas generator;
a first baffle portion extending along an axial length of said casing, said first baffle portion extending radially outwardly from an outer surface of the casing;
a second baffle portion extending at least partially radially outwardly from said first baffle portion, said second baffle portion comprising:
a radially inner edge supported by said first baffle portion; and
a radially outer edge extending proximate an inner surface of a radially outer cowl; and
a gap extending between said radially outer edge and said inner surface.

10. The gas turbine engine of claim 9 , wherein said casing includes a cylindrical cross-section.

11. The gas turbine engine of claim 9 , wherein said cowl includes a cylindrical cross-section concentric with a longitudinal axis of said casing.

12. The gas turbine engine of claim 9 , wherein said radially inner edge is coupled to a radially outer edge of said first baffle portion.

13. The gas turbine engine of claim 9 , wherein said radially inner edge of said second baffle portion is spaced circumferentially said radially outer edge of said first baffle portion.

14. The gas turbine engine of claim 9 , further comprising a spacer positioned between said radially inner edge of said second baffle portion and said radially outer edge of said first baffle portion, said spacer configured to maintain a gap between said radially inner edge of said second baffle portion and said radially outer edge of said first baffle portion.

15. The gas turbine engine of claim 9 , further comprising a seal between said cowl and said radially outer edge of said second baffle portion.

16. The gas turbine engine of claim 9 , further comprising at least one of a brush seal and a bulb seal between said cowl and said radially outer edge of said second baffle portion.

17. A method of forming a gas turbine engine fan compartment fire baffle, said method comprising:
coupling a first baffle portion along an axial length of a casing, the first baffle portion including a first radially inner edge, a first radially outer edge, and a first body extending therebetween, the casing forming a radially inner surface of the fan compartment, the first baffle portion extending radially outwardly from an outer surface of the casing;
coupling a second baffle portion to the radially outer edge, the second baffle portion extending at least partially radially outwardly from the first radially outer edge, the second baffle portion including:
a second radially inner edge supported by the first radially outer edge; and
a second radially outer edge extending proximate an inner surface of a radially outer cowl, the radially outer cowl forming a radially outer surface of the fan compartment; and
maintaining a gap that extends between the second radially outer edge and the inner surface of the outer cowl.

18. The method of claim 17 , wherein coupling a first baffle portion along an axial length of a casing comprises coupling a first baffle portion along an axial length of a casing formed of a composite material.

19. The method of claim 17 , wherein coupling a plurality of first baffle portions along an axial length of the casing, each of the plurality of first baffle portions spaced circumferentially about the outer surface of the casing.

20. The method of claim 17 , wherein coupling a first baffle portion along an axial length of a casing comprises coupling a first baffle portion formed of at least one of a composite material and titanium along an axial length of the casing.

Assignees

• Gen Electric

Inventors

• Grose Kyle Andrew
• Hegeman Arjan Johannes
• Kemp Andrew David
• Pyles John Michael

Classifications

• F05D2260/231

  Preventing heat transfer · CPC title

• F01D25/24 Primary

  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 title

• Y02T50/672

  Cross-Sectional Technologies · mapped topic

• F02C7/25

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

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title