Systems and methods for a variable geometry turbine nozzle

Patent metadata

Field	Value
Publication number	US-9890700-B2
Application number	US-201514709339-A
Country	US
Kind code	B2
Filing date	May 11, 2015
Priority date	Nov 21, 2014
Publication date	Feb 13, 2018
Grant date	Feb 13, 2018

Abstract

Various systems and methods are described for a variable geometry turbine. In one example, a nozzle vane includes a stationary having a first cambered sliding surface and a sliding vane having a second cambered sliding surface where the second cambered sliding surface includes a flow disrupting feature in contact with the first sliding cambered surface. The sliding vane may be positioned to slide in a direction from substantially tangent along a curved path to an inner circumference of the turbine nozzle and selectively uncover the flow disrupting feature.

First claim

The invention claimed is:

1. A turbine nozzle, comprising:
a nozzle vane including:
a stationary vane attached to a surface of a nozzle wall plate and including a first sliding surface; and
a sliding vane including a second sliding surface including a flow disrupting feature in contact with the first sliding surface, the sliding vane positioned to slide in a direction from substantially tangent to an inner circumference of the turbine nozzle and selectively uncover the flow disrupting feature.

2. The nozzle of claim 1 , wherein the first sliding surface and the second sliding surface are cambered surfaces and wherein the sliding vane is positioned to slide along a curved line matching the cambered surfaces of the first sliding surface and the second sliding surface.

3. The nozzle of claim 1 , wherein the sliding vane slides on a curved path defined by a curvature of the first sliding surface and the second sliding surface.

4. The nozzle of claim 1 , wherein the flow disrupting feature is a plurality of flow disrupting features each adjacent to a respective trailing edge of a plurality of nozzle vanes.

5. The nozzle of claim 1 , wherein the flow disrupting feature includes a groove or a dimple.

6. The nozzle of claim 1 , wherein the flow disrupting feature includes two or more parallel grooves each having a substantially triangular cross section or substantially rectangular cross section.

7. The nozzle of claim 1 , wherein the flow disrupting feature occupies approximately 10% to 40% of the sliding vane.

8. The nozzle of claim 1 , wherein at large vane openings where the sliding vane is extended and moved away from the stationary vane, the flow disrupting feature is uncovered and exposed to gas flow.

9. The nozzle of claim 1 , wherein at small vane openings where the sliding vane is not extended away from the stationary vane, the flow disrupting feature is fully covered by the sliding vane.

10. The nozzle of claim 1 , wherein a ratio of a maximum nozzle thickness of the nozzle vane to a length of a chord of the nozzle vane is greater than 0.35.

11. A method, comprising:
adjusting a position of a plurality of adjustable vanes radially positioned around a turbine wheel of a variable geometry turbine to a first position exposing a flow disrupting feature on a portion of a surface of each of the plurality of adjustable vanes; and
adjusting the position of the plurality of adjustable vanes to a second position covering the flow disrupting feature so that the flow disrupting feature is not exposed to gas flow.

12. The method of claim 11 , wherein the adjusting the position of the plurality of adjustable vanes to the first position includes adjusting the position of the plurality of adjustable vanes to the first position in response to engine load less than a threshold load.

13. The method of claim 11 , wherein the adjusting the position of the plurality of adjustable vanes to the second position includes adjusting the position of the plurality of adjustable vanes to the second position in response to engine load greater than a threshold load.

14. The method of claim 11 , wherein the plurality of adjustable vanes includes a stationary vane portion and a sliding vane portion, wherein the flow disrupting feature is on a first sliding surface of the sliding vane portion, and wherein the first sliding surface slides against a second sliding surface of the stationary vane portion.

15. The method of claim 14 , wherein the first sliding surface and the second sliding surface are curved surfaces and wherein the first sliding surface slides against the second sliding surface along a curved path defined by the curved surfaces.

Assignees

• Ford Global Tech Llc

Inventors

• Sun Harold Huimin
• Zhao Ben
• Hu Leon
• Yi Jianwen James
• Curtis Eric Warren
• Zhang Jizhong

Classifications

• F01D17/165 Primary

  for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line (F01D17/167 takes precedence) · CPC title

• F02B37/24 Primary

  by using pumps or turbines with adjustable guide vanes · CPC title

• F05D2210/30

  Flow characteristics · CPC title

• F05D2220/40

  in turbochargers · CPC title

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title