Fluid diodes with ridges to control boundary layer in axial compressor stator vane

Patent metadata

Field	Value
Publication number	US-10519976-B2
Application number	US-201715401953-A
Country	US
Kind code	B2
Filing date	Jan 9, 2017
Priority date	Jan 9, 2017
Publication date	Dec 31, 2019
Grant date	Dec 31, 2019

Abstract

An entrance stator in a turbofan has an airfoil shape with a leading edge and a trailing edge connected by surfaces which define a suction side and a pressure side. The entrance stator has a channel with an opening on the pressure side, extending to an exit on the suction side, having a pressure gradient between the opening and the exit. The channels are preceded with a ridge. The channels and the ridges control the boundary layer, enabling higher efficiencies. The channels and ridges add energy to the boundary layer to prevent separation.

First claim

I claim:

1. A turbofan comprising:
a inlet passage;
a fan in the inlet passage, the inlet passage separating into a bypass passage and core passage downstream of the fan;
the core passage having an entrance proximate to the fan and an outlet downstream of a compressor;
an entrance stator located within the core passage aft of the entrance and forward of the compressor; the entrance stator fixed to an inner casing and an outer casing, the entrance stator extending radially between the inner and outer casing; the outer casing separating the bypass passage from the core passage;
the entrance stator having an airfoil shape with a leading edge and a trailing edge connected by surfaces which define a suction side and a pressure side;
the entrance stator having a channel with an opening on the pressure side, the channel extending from the opening to an exit on the suction side, wherein there is a pressure gradient between the opening and the exit, wherein the pressure gradient ensures flow from the opening on the pressure side to the exit on the suction side.

2. The turbofan according to claim 1 , wherein the exit of the channel is located proximate the inner casing and wherein the inner and outer casing are co-axial.

3. The turbofan according to claim 1 , wherein the exit of the channel extends radially from the inner casing to less than a third of the stator span.

4. The turbofan according to claim 1 , wherein the exit of the channel is located forward of a half chord of the entrance stator.

5. The turbofan according to claim 1 , wherein the exit of the channel is located aft of the half chord of the entrance stator.

6. The turbofan according to claim 1 , further comprising a ridge located on the surface of the suction side of the entrance stator, adjacent and forward of the channel exit, the ridge extending into the core passage.

7. The turbofan according to claim 1 , wherein the entrance stator comprises a second channel, the second channel with a second opening on the pressure side and a second exit on the suction side.

8. The turbofan according to claim 1 , wherein the exit is polygonal with at least one side perpendicular to a predetermined flow proximate to the exit.

9. The turbofan according to claim 1 , where the size of the opening is greater than the exit.

10. In a turbofan with a plurality of stators between a fan and a rotor of a compressor, wherein the fan and compressor rotor are coaxial, each stator having a leading edge, trailing edge, suction surface and pressure surface, the suction and pressure surfaces extending between the leading and trailing edge; a method of increasing the efficiency of the compressor comprising:
injecting high pressure air from the pressure surface via a passage between the pressure surface and the suction surface into a boundary layer on the suction surface,
restricting the flow of fluid from the suction surface through the passage towards the pressure surface;
tripping the fluid flow proximate a boundary layer on the suction surface from laminar to turbulent on the suction surface upstream of the injected high pressure air, thereby increasing the efficiency of the compressor.

11. The method according to claim 10 , further comprising exposing the passage to the high pressure fluid proximate the surface forward of a half chord of each of the plurality of stators.

12. The method according to claim 10 , wherein the passage exits the suction surface aft of the half chord of the stator.

13. The method according to claim 10 , wherein the step of tripping the air flow comprises positioning a ridge on the suction surface of each stator forward of the passage and extending the ridge into the air flow.

14. The method according to claim 10 , wherein the passage comprises multiple passages.

15. The method according to claim 10 , further comprising positioning the passage's exit proximate to a predetermined fluid flow detachment region on the suction surface.

16. The method according to claim 15 , further comprising positioning the passage on the pressure surface at a region where the fluid proximate the region creates a pressure gradient to drive the fluid to the suction surface.

17. A stator vane comprising:
a leading edge, trailing edge, a first surface from the leading edge to the trailing edge and a second surface oppositely disposed from the first surface extending from the trailing edge to the leading edge in the shape of an aerofoil;
a one-way channel with an opening on the first surface, the one-way channel extending from the opening to an exit on the second surface,
a pressure gradient between the opening and the exit of the one-way channel; and,
a ridge extending from the second surface forward of the exit, proximate to the opening and the exit;
wherein the first surface is in fluid communication via the one-way channel with the second surface, and wherein the pressure gradient ensures flow from the opening on the pressure side to the exit on the suction side.

18. The stator vane according to claim 17 , wherein the exit is polygonal and at least one of the sides extends along the span of the vane.

19. The stator vane according to claim 17 , further comprising a second one-way channel with a second opening on the first side, the second one-way channel extending from the second opening to a second exit on the second surface.

20. The stator vane according to claim 17 , wherein first and second exits are positioned in an area predetermined to have low momentum flow.

Assignees

• Rolls Royce Corp

Inventors

• Shimo Masayoshi

Classifications

• F01D5/146

  of blades with tandem configuration, split blades or slotted blades · CPC title

• F02K3/06

  with front fan · CPC title

• F04D29/325

  for axial flow fans (blade mountings F04D29/34, blades F04D29/38) · CPC title

• F05D2240/124

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

• F04D29/544 Primary

  Blade shapes · CPC title