Airfoil contour for low-loss on-boarding of cooling air through an articulating spindle

Patent metadata

Field	Value
Publication number	US-2016290158-A1
Application number	US-201415034951-A
Country	US
Kind code	A1
Filing date	Nov 3, 2014
Priority date	Nov 14, 2013
Publication date	Oct 6, 2016
Grant date	—

Abstract

A turbine stator vane assembly for a gas turbine engine is disclosed and includes an airfoil rotatable about an axis transverse to an engine longitudinal axis. The airfoil includes outer walls defining an inner chamber between a pressure side and a suction side of the airfoil. At least one spindle supports rotation of the airfoil and includes a feed opening for communicating cooling air into the inner chamber. An inlet defines a passage between the feed opening and the inner chamber and includes a protrusion of the outer wall on at least one of the pressure side and suction side of the airfoil.

First claim

What is claimed is:

1 . A vane assembly for a gas turbine engine comprising:
an airfoil rotatable about an axis transverse to an engine longitudinal axis, the airfoil including outer walls defining an inner chamber between a pressure side and a suction side of the airfoil; and at least one spindle supporting rotation of the airfoil, the at least one spindle including feed opening for communicating cooling air into the inner chamber; and an inlet defining a passage between the feed opening and the inner chamber, the inlet defined by a protrusion of the outer wall on at least one of the pressure side and suction side of the airfoil.

2 . The vane assembly as recited in claim 1 , wherein the protrusion extends outward from a pressure side of the airfoil.

3 . The vane assembly as recited in claim 1 , wherein the protrusion extends outward from a suction side of the airfoil.

4 . The vane assembly as recited in claim 1 , wherein the at least one spindle comprises an outer spindle and an inner spindle each including a feed opening and the inlet comprises an outer inlet and an inner inlet each forming a protrusion on the outer wall.

5 . The vane assembly as recited in claim 1 , wherein the passage defined by the inlet tapers from a first width defined by the feed opening to a second width smaller than the first width defined by the inner chamber.

6 . The vane assembly as recited in claim 1 , wherein the protrusion comprises an ellipsoid shape extending from at least one of the pressure side and suction side of the airfoil.

7 . The vane assembly as recited in claim 1 , wherein the pressure side and suction side extend a first radial length from an inner side to an outer side and the protrusion is less than the first length.

8 . The vane assembly as recited in claim 1 , wherein the protrusion comprises a first protrusion extending radially inward from the outer side and a second protrusion extending radially outward from the inner side.

9 . The vane assembly as recited in claim 1 , including an outer platform and an inner platform with the airfoil supported between the outer platform and the inner platform.

10 . The vane assembly as recited in claim 9 , including a fixed airfoils supported between the inner platform and the outer platform adjacent the airfoil.

11 . A turbine section of a gas turbine engine comprising;
at least one rotor supporting rotation of a plurality of blades about an engine longitudinal axis; and at least one variable vane rotatable about an axis transverse to the engine rotational axis for varying a direction of airflow, the variable vane including an airfoil rotatable about an axis transverse to an engine longitudinal axis, the airfoil including outer walls defining an inner chamber between a pressure side and a suction side of the airfoil, at least one spindle supporting rotation of the airfoil, the at least one spindle including feed opening for communicating cooling air into the inner chamber, and an inlet defining a passage between the feed opening and the inner chamber, the inlet defined by a protrusion of the outer wall on at least one of the pressure side and suction side of the airfoil.

12 . The turbine section as recited in claim 11 , wherein the at least one spindle comprises an outer spindle and an inner spindle each including a feed opening and the inlet comprises an outer inlet and an inner inlet each forming a protrusion on the outer wall.

13 . The turbine section as recited in claim 11 , wherein the passage defined by the inlet tapers from a first width defined by the feed opening to a second width smaller than the first width defined by the inner chamber.

14 . The turbine section as recited in claim 11 , wherein the protrusion comprises an ellipsoid shape extending from at least one of the pressure side and suction side of the airfoil.

15 . The turbine section as recited in claim 11 , including an outer platform and an inner platform with the variable vane supported adjacent a fixed vane between the outer platform and the inner platform.

16 . The turbine section as recited in claim 15 , including a plurality of variable vanes and a plurality of fixed vanes defining a vane stage of the turbine section and alternating about the engine longitudinal axis.

17 . A gas turbine engine comprising:
a compressor section; a combustor in fluid communication with the compressor section; and a turbine section in fluid communication with the combustor; the turbine section including at least one rotor supporting rotation of a plurality of blades about an engine longitudinal axis; and at least one variable vane rotatable about an axis transverse to the engine rotational axis for varying a direction of airflow, the variable vane including an airfoil rotatable about an axis transverse to an engine longitudinal axis, the airfoil including outer walls defining an inner chamber between a pressure side and a suction side of the airfoil, at least one spindle supporting rotation of the airfoil, the at least one spindle including feed opening for communicating cooling air into the inner chamber, and an inlet defining a passage between the feed opening and the inner chamber, the inlet defined by a protrusion of the outer wall on at least one of the pressure side and suction side of the airfoil.

18 . The gas turbine engine as recited in claim 17 , wherein the at least one spindle comprises an outer spindle and an inner spindle each including a feed opening and the inlet comprises an outer inlet and an inner inlet each forming a protrusion on the outer wall.

19 . The gas turbine engine as recited in claim 17 , wherein the passage defined by the inlet tapers from a first width defined by the feed opening to a second width smaller than the first width defined by the inner chamber.

20 . The gas turbine engine as recited in claim 17 , including an outer platform and an inner platform with the variable vane supported adjacent a fixed vane between the outer platform and the inner platform.

Assignees

• United Technologies Corp

Inventors

• Slavens Thomas N
• Grover Eric A
• Teixeira John D

Classifications

• F01D9/065

  Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26) · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• F01D25/12 Primary

  Cooling · CPC title

• F01D9/04

  forming ring or sector · CPC title