Systems and Methods Involving Variable Vanes

• US 20090016871A1
• Filed: 07/10/2007
• Published: 01/15/2009
• Est. Priority Date: 07/10/2007
• Status: Abandoned Application

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: McCaffrey, Michael G.
• Application Number:
  US11/775,523
• Publication Number:
  US 20090016871A1
• Time in Patent Office: Days
• US Class Current: 415/115
• CPC Class Codes: F01D 5/145 Means for influencing boundary layers or secondary circulations for compressors F04D29/68
• CPC Class Codes: F01D 5/146 of blades with tandem configuration, split blades or slotted blades
• CPC Class Codes: F01D 5/148 Blades with variable camber, e.g. by ejection of fluid
• CPC Class Codes: F01D 9/04 forming ring or sector
• CPC Class Codes: F05D 2270/17 to control boundary layer

Abstract

Systems and methods involving vanes are provided. In this regard, a representative method for modifying the throat area between vanes of a gas turbine engine includes: directing a gas flow path of the gas turbine engine between a first vane and a second vane, wherein each of the first vane and the second vane has an outer surface and an interior; and emitting pressurized air from outlet ports communicating between the outer surface and the interior of the first vane, wherein the emitted pressurized air from the first vane modifies a throat area between the first vane and the second vane.

Claims

1. A gas turbine engine defining a gas flow path, the gas turbine engine comprising:

a first vane extending into the gas flow path and having;

an interior operative to receive pressurized air;

an outer surface; and

outlet ports communicating between the outer surface and the interior of the first vane, the outlet ports being operative to receive the pressurized air from the interior and emit the pressurized air into the gas flow path such that a throat area defined, at least in part, by the first vane is modified.

2. The turbine engine of claim 1, wherein the throat area is modified by moving the throat area upstream.

3. The turbine engine of claim 1, wherein the first vane further comprises film cooling ports operative to receive cooling pressurized air at a pressure lower than that provided to the outlet ports and to emit the cooling pressurized air from the first vane such that the first vane is film cooled.

4. The turbine engine of claim 1, further comprising a valve assembly operative to regulate the pressurized air emitted by the ports.

5. The turbine engine of claim 1, further comprising a second vane, the throat area being defined by the first vane and the second vane.

6. The turbine engine of claim 5, further comprising a valve assembly operative to control the pressurized air emitted by the first vane and the second vane.

7. The turbine engine of claim 6, further comprising a second throat area defined, at least in part, by the second vane, wherein the throat area and the second throat area are modified independently by the valve assembly.

8. The turbine engine of claim 1, wherein the valve assembly is operative to intermittently provide the pressurized air to the ports.

9. The turbine engine of claim 1, wherein the engine is a turbofan.

10. A vane assembly comprising:

a first vane having;

an outer surface;

an interior defining a cavity operative to receive pressurized air; and

outlet ports communicating between the outer surface and the cavity, the outlet ports being operative to receive the pressurized air from the cavity and emit the pressurized air through the outer surface a valve assembly operative to regulate the pressurized air emitted by the first vane.

11. The vane assembly of claim 10, further comprising a control assembly operative to control the valve assembly.

12. The vane assembly of claim 10, further comprising:

a second vane operative to define a throat area between the first vane and the second vane, wherein the pressurized air emitted from the outlet ports of the first vane is operative to modify the throat area between the first vane and the second vane.

13. The vane assembly of claim 10, wherein the first vane further comprises film cooling ports operative to receive cooling pressurized air at a pressure lower than that provided to the outlet ports and to emit the cooling pressurized air from the first vane such that the first vane is film cooled.

14. The vane assembly of claim 10, wherein the valve assembly comprises a piston and a solenoid, the piston and the solenoid being operative to increase the pressure of air provided to the valve assembly.

15. A method for modifying the throat area between vanes of a gas turbine engine comprising:

directing a gas flow path of the gas turbine engine between a first vane and a second vane, wherein each of the first vane and the second vane has an outer surface and an interior; and

emitting pressurized air from outlet ports communicating between the outer surface and the interior of the first vane, wherein the emitted pressurized air from the first vane modifies a throat area between the first vane and the second vane.

16. The method of claim 15, further comprising film cooling the first vane using lower pressure air than the emitted pressurized air used to modify the throat area.

17. The method of claim 15, wherein the step of emitting the pressurized air from outlet ports further comprises emitting the pressurized air in pulses.

18. The method of claim 15, further comprising emitting pressurized air from outlet ports communicating between the outer surface of the second vane and the interior of the second vane such that the emitted pressurized air from the second vane also modifies the throat area between the first vane and the second vane.

19. The method of claim 15, wherein the step of emitting the pressurized air from outlet ports further comprises emitting the pressurized air in a direction corresponding to the flow of the gas flow path.

20. The method of claim 15, wherein the step of emitting the pressurized air from ports further comprises emitting the pressurized air to reduce engine resonance.