Turbine vane rear insert scheme

Patent metadata

Field	Value
Publication number	US-10247034-B2
Application number	US-201514813585-A
Country	US
Kind code	B2
Filing date	Jul 30, 2015
Priority date	Jul 30, 2015
Publication date	Apr 2, 2019
Grant date	Apr 2, 2019

Abstract

An internally cooled turbine vane for a gas turbine engine has coolant flow channels between the interior walls of the vane and an insert, where the channels serve to convey a portion of the cooling air flow from a pressure side chamber to a suction side chamber. The turbine vane defines a radially extending passage with a dividing wall defining a front section and a rear section; the rear section having interior walls spaced apart from an insert to define the pressure side chamber and the suction side chamber. The insert may receive cooling air and conveys the cooling air into the pressure side chamber and the suction side chamber. A front surface of the insert or a rear surface of the dividing wall may have a clearance gap and an air flow channel communicating between the pressure side chamber and the suction side chamber.

First claim

We claim:

1. A turbine vane comprising:
a pressure side; a suction side; and a hollow front section separated from a hollow rear section by a dividing wall;
the hollow rear section having interior walls spaced apart from a hollow insert by stand-offs to define a pressure side chamber and a suction side chamber, the hollow insert being separate from the interior walls and independently positioned in the hollow rear section;
the hollow insert adapted to be in fluid communication with a source of pressurized cooling air and having openings for conveying cooling air into the pressure side chamber and the suction side chamber, the hollow insert being tubular and having a closed downstream end, the pressure side chamber and the suction side chamber merging in flow communication at the closed downstream end of the hollow insert;
a front surface of the hollow insert and a rear surface of the dividing wall being spaced apart defining a gap; and
at least one of: a) the front surface of the hollow insert or b) the rear surface of the dividing wall, having a channel formed therein, the channel communicating between the pressure side chamber and the suction side chamber.

2. The turbine vane according to claim 1 , wherein the channel comprises a recess formed within the rear surface of the dividing wall.

3. The turbine vane according to claim 1 , wherein the channel comprises a dimple within the front surface of the insert.

4. The turbine vane according to claim 1 , comprising two channels radially spaced apart.

5. The turbine vane according to claim 4 , wherein the two channels are disposed at radially opposed end portions of the vane.

6. The turbine vane according to claim 5 , wherein the two channels are disposed upstream from regions on the suction side of the turbine vane that are exposed to lower gas path temperatures relative to higher gas path temperatures of a central region.

7. The turbine vane according to claim 1 , comprising a throttle in the pressure side chamber.

8. The turbine vane according to claim 7 , wherein the throttle comprises radially extending aerodynamic trips located in a downstream portion of the pressure side chamber.

9. The turbine vane according to claim 7 , wherein the throttle comprise pins adjacent one of: an upstream; and a downstream portion, of the pressure side chamber having a larger radial dimension relative to a radial dimension of the stand-offs.

10. The turbine vane according to claim 7 , wherein the throttle comprises one of: radially extending pedestals; and axially extending ribs, disposed at a downstream end of the pressure side chamber.

11. An internally cooled turbine vane comprising:
a pressure side; a suction side; and a radially extending passage defined between the pressure side and the suction side, the radially extending passage defined by interior walls of the vane;
an insert separately positioned in the radially extending passage and defining therewith a pressure side chamber and a suction side chamber, the insert having a tubular body with a closed downstream end, the pressure side chamber and the suction side chamber merging in flow communication at the closed downstream end of the insert, the tubular body spaced from the interior walls by stand-offs;
a front surface of the insert and/or one of the interior walls of the vane that faces the front surface of the insert having at least one channel formed therein, the at least one channel communicating between the pressure side chamber and the suction side chamber; and
a flow restrictor for directing a portion of a coolant within the pressure side chamber through the at least one channel to the suction side chamber by a pressure differential between the pressure and suction side chambers, the flow restrictor configured to increase air pressure in the pressure side chamber to a value greater than the air pressure in the suction side chamber.

12. The internally cooled turbine vane according to claim 11 , wherein the at least one channel comprises a recess formed within a surface of an internal dividing wall of the internally cooled turbine vane.

13. The internally cooled turbine vane according to claim 11 , wherein the at least one channel comprises a dimple within a front surface of the insert.

14. The internally cooled turbine vane according to claim 11 , wherein the at least one channel comprises two channels radially spaced apart.

15. The internally cooled turbine vane according to claim 14 , wherein the two channels are disposed adjacent an outer end and an inner end of the radially extending passage of the internally cooled turbine vane.

16. The internally cooled turbine vane according to claim 15 , wherein the two channels are disposed upstream from regions on the suction side of the internally cooled turbine vane that are exposed to lower gas path temperatures relative to higher gas path temperatures of a central region.

17. The internally cooled turbine vane according to claim 11 , wherein the flow restrictor comprise a throttle between the pressure side chamber and a trailing edge outlet.

18. The internally cooled turbine vane according to claim 17 , wherein the throttle comprise radially extending aerodynamic trips at a downstream end of the pressure side chamber.

19. The internally cooled turbine vane according to claim 17 , wherein the throttle comprises protrusions adjacent one of: an upstream; and a downstream portion, of the pressure side chamber having a larger radial dimension relative to a radial dimension of other protrusions.

20. The internally cooled turbine vane according to claim 17 , wherein the throttle comprises one of: radially extending pedestals; and axially extending ribs, disposed upstream of the trailing edge outlet inside the pressure side chamber.

21. An internally cooled turbine vane comprising:
a pressure side; a suction side; and a radially extending passage defined between the pressure side and the suction side, the radially extending passage defined by interior walls of the vane;
an insert separately positioned in the radially extending passage and defining therewith a pressure side chamber and a suction side chamber, the insert having a tubular body with a closed downstream end, the pressure side chamber and the suction side chamber merging in flow communication at the closed downstream end of the insert, the tubular body spaced from the interior walls by stand-offs, the stand-offs extending along longitudinal axes between the interior walls and the tubular body;
at least one channel communicating between the pressure side chamber and the suction side chamber; and
a flow restrictor for directing a portion of a coolant within the pressure side chamber through the at least one channel to the suction side chamber by a pressure differential between the pressure and suction side chambers, the flow restrictor configured to increase air pressure in the pressure side chamber to a value greater than the air pressure in the suction side chamber, the flow restrictor including aerodynamic trips, the aerodynamic trips secured to the stand-offs and extending radially therefrom relative to the longitudinal axes.

22. The internally cooled turbine vane of claim 21 , wherein the aerodynamic trips extend parallel to a longitudinal axis of the tubular body of the insert.

Assignees

• Pratt & Whitney Canada

Inventors

• Papple Michael
• Lebel Larry

Classifications

• F05D2260/202

  by film cooling · CPC title

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F05D2240/124

  related to the suction side of a stator vane · CPC title

• F05D2260/201

  by impingement of a fluid · CPC title