Gas turbine engine with an offtake

Patent metadata

Field	Value
Publication number	US-2017321602-A1
Application number	US-201715440199-A
Country	US
Kind code	A1
Filing date	Feb 23, 2017
Priority date	Mar 9, 2016
Publication date	Nov 9, 2017
Grant date	—

Abstract

An apparatus and method are disclosed for a gas turbine engine including an offtake located within the air flow of the engine. The offtake has an inlet and a louver covering the inlet. The louver has multiple airfoils arranged to direct the air flow into the inlet of the offtake.

First claim

What is claimed is:

1 . A gas turbine engine comprising:
an annular fan exhaust section; an engine core at least partially located within the fan exhaust section; a cooling air offtake located in the engine core and having an inlet; and a louver located at the inlet and having at least two different size airfoils in spaced axial arrangement.

2 . The gas turbine engine of claim 1 , wherein the at least two different size airfoils comprise an initial airfoil upstream of a primary airfoil, the primary airfoil having a chord and a max height greater than the initial airfoil.

3 . The gas turbine engine of claim 2 , wherein the chord of the primary airfoil is at least 2.5 times greater than the chord of the initial airfoil.

4 . The gas turbine engine of claim 3 , wherein the max height of the primary airfoil is at least 2 times greater than the max height of the initial airfoil.

5 . The gas turbine engine of claim 2 , further comprising third and fourth airfoils downstream of the primary airfoil.

6 . The gas turbine engine of claim 5 , wherein the third and fourth airfoils have chords that are smaller than the chord of the primary airfoil.

7 . The gas turbine engine of claim 6 , wherein the third airfoil has a chord that is greater than the chord of the initial and fourth airfoils.

8 . The gas turbine engine of claim 7 , wherein an angle of attack of the third and fourth airfoils is greater than the angle of attack of the initial and primary airfoils.

9 . The gas turbine engine of claim 7 , wherein a leading edge of the inlet has a rounded lip.

10 . The gas turbine engine of claim 9 , wherein a trailing edge of the inlet has a chamfer.

11 . The gas turbine engine of claim 1 , wherein the at least two different size airfoils are shaped to provide a pressure recovery of at least 0.3.

12 . The gas turbine engine of claim 11 , wherein the pressure recovery is at least 0.34.

13 . A louver assembly for an off take of a gas turbine engine comprising at least four airfoils in axial arrangement, wherein none of the airfoils are of the same size.

14 . The louver assembly of claim 13 , wherein a second of the four airfoils is a primary airfoil having a chord greater than a chord of any of the other four airfoils.

15 . The louver assembly of claim 14 , wherein the primary airfoil has a chord at least X times greater than the chord of a first airfoil.

16 . The louver assembly of claim 15 , wherein the primary airfoil has a chord at least Y times greater than the chord of a third and fourth airfoils.

17 . The louver assembly of claim 16 , wherein the third and fourth airfoils have a different angle of attack than the first and second airfoils.

18 . The louver assembly of claim 17 , wherein the fourth airfoil has a chord less than the third airfoil.

19 . The louver assembly of claim 18 , wherein the louver has a leading edge in the form of a rounded lip, and a trailing edge in the form of a chamfer.

20 . The louver assembly of claim 19 , wherein the at least four different size airfoils are shaped to provide a pressure recovery of at least 0.3.

Assignees

• Gen Electric

Inventors

• Guijarro Valencia Antonio
• Michelassi Vittorio

Classifications

• F02C7/18 Primary

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title

• F01D9/023

  Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings · CPC title

• B64D2033/0286

  for turbofan engines · CPC title

• F02C7/14

  of fluids in the plant {, e.g. lubricant or fuel (F02C7/185 takes precedence)} · CPC title

• B64D33/02

  of combustion air intakes · CPC title