Oil tank installation in gas turbine engine

Patent metadata

Field	Value
Publication number	US-10816007-B2
Application number	US-201615349281-A
Country	US
Kind code	B2
Filing date	Nov 11, 2016
Priority date	Nov 11, 2016
Publication date	Oct 27, 2020
Grant date	Oct 27, 2020

Abstract

Oil tanks for gas turbine engines and associated assembly methods are disclosed. In one exemplary embodiment, an oil tank is configured to be installed to occupy a radially-inner space defined by an annular radial air inlet duct of a reverse flow gas turbine engine. The oil tank may comprise a first tank portion and a second tank portion assembled together to cooperatively define an interior volume of the tank. An optional intermediate spacer may be disposed between the first tank portion and the second tank portion in order to form an oil tank of a larger size.

First claim

What is claimed is:

1. A gas turbine engine comprising:
an annular radial air inlet duct configured to receive a flow of air along a generally radially inward direction relative to an axis of the engine and direct the air toward a substantially axial direction relative to the axis, the annular radial air inlet duct comprising an inner duct wall defining a radially-inner space having a radially outer dimension that diminishes in the axial direction;
a compressor communicating with the annular radial air inlet duct; and
an oil tank in communication with one or more engine lubrication loads, wherein:
the oil tank is at least partially disposed in the radially-inner space;
the oil tank has an interior tank volume that intersects the axis at an axial location within the radially-inner space;
the oil tank has a tank wall that is spaced apart from the duct wall and that faces the duct wall;
the tank wall is substantially axisymmetric about the axis; and
the tank wall defines a radially-outer dimension of the oil tank that diminishes in the axial direction to at least partially conform to a shape of the duct wall.

2. The gas turbine engine as defined in claim 1 , wherein the axis is an axis of rotation of the compressor.

3. The gas turbine engine as defined in claim 1 , wherein the oil tank has an outer periphery that is substantially circular when viewed along the axis.

4. The gas turbine engine as defined in claim 1 , wherein a gap between the tank wall and the duct wall is substantially uniform across at least a majority of the tank wall facing the duct wall.

5. The gas turbine engine as defined in claim 1 , wherein the radially-inner space defined by the duct wall is radially converging in a forward direction of the engine along the axis.

6. The gas turbine engine as defined in claim 1 , wherein the gas turbine engine is a reverse flow gas turbine engine.

7. The gas turbine engine as defined in claim 1 , wherein the oil tank is disposed aft of the compressor in the engine.

8. The gas turbine engine as defined in claim 1 , wherein:
the axis is an axis of rotation of the compressor; and
the annular radial air inlet duct is disposed aft of the compressor relative to the axis.

9. The gas turbine engine as defined in claim 8 , wherein the oil tank comprises a forward tank portion assembled with an aft tank portion to cooperatively define the internal tank volume.

10. The gas turbine engine as defined in claim 8 , wherein:
the oil tank comprises a forward tank portion and an aft tank portion;
the forward tank portion is configured to be assembled with the aft tank portion to cooperatively define an internal tank volume of a first size; and
the forward tank portion is configured to be assembled with the aft tank portion via an optional spacer disposed between the forward tank portion and the aft tank portion so that the forward tank portion, the aft tank portion and the spacer cooperatively define an internal tank volume greater than the first size.

11. The gas turbine engine as defined in claim 1 , wherein a gap between the tank wall and the duct wall extends across substantially all of the tank wall.

12. An assembly for installation in a gas turbine engine, the assembly comprising:
an annular radial air inlet duct configured to receive a flow of air along a generally radially inward direction relative to an axis of the engine and direct the air toward a substantially axial direction relative to the axis and toward a compressor of the gas turbine engine, the annular radial air inlet duct comprising an inner duct wall defining a radially-inner space disposed centrally within the annular radial air inlet duct, the radially-inner space having a radially outer dimension that diminishes in the axial direction; and
an oil tank at least partially disposed in the radially-inner space defined by the inner duct wall, the oil tank having an interior tank volume that intersects the axis at an axial location within the radially-inner space, the oil tank having a tank wall that is spaced apart from the duct wall and that faces the duct wall, the tank wall being substantially axisymmetric about the axis, the tank wall defining a radially-outer dimension of the oil tank that diminishes in the axial direction to at least partially conform to a shape of the duct wall.

13. The assembly as defined in claim 12 , wherein a gap between the tank wall and the duct wall is substantially uniform across at least a majority of the tank wall facing the duct wall.

14. The assembly as defined in claim 13 , wherein the axis corresponds to a central axis of the gas turbine engine when the radial air inlet duct is installed in the gas turbine engine and the radially-inner space is radially converging in a forward direction along the axis.

15. The assembly as defined in claim 12 , wherein:
the oil tank comprises a forward tank portion and an aft tank portion;
the forward tank portion is configured to be assembled with the aft tank portion to cooperatively define an internal tank volume of a first size; and
the forward tank portion is configured to be assembled with the aft tank portion via an optional spacer disposed between the forward tank portion and the aft tank portion so that the forward tank portion, the aft tank portion and the spacer cooperatively define an internal tank volume greater than the first size.

16. An oil tank for installation in a gas turbine engine and configured to be at least partially disposed in a radially-inner space defined by an inner duct wall of an annular radial air inlet duct where the annular radial air inlet duct is configured to receive a flow of air along a generally radially inward direction relative to an axis of the engine and direct the air toward a substantially axial direction relative to the axis, the radially-inner space wall having a radially outer dimension that diminishes in the axial direction, the oil tank comprising:
a forward tank portion and an aft tank portion cooperatively defining an internal tank volume that intersects the axis when installed in the gas turbine engine, the forward tank portion comprising a tank wall configured to face the inner duct wall and be spaced apart from the inner duct wall, the tank wall being substantially axisymmetric about the axis, the tank wall defining a radially-outer dimension of the oil tank that diminishes in the axial direction to at least partially conform to a shape of the inner duct wall.

17. The oil tank as defined in claim 16 , wherein the forward tank portion and the aft tank portion are assembled at a substantially circular interface.

Assignees

• Pratt & Whitney Canada

Inventors

• Desjardins Michel
• Bonacorsi Francis
• Morgan Keith

Classifications

• F01D25/18 Primary

  Lubricating arrangements (of machines or engines in general F01M) · CPC title

• F04D29/063 Primary

  specially adapted for elastic fluid pumps · CPC title

• F04D29/545

  Ducts · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F04D29/644

  especially adapted for elastic fluid pumps · CPC title