Systems and methods for a variable geometry turbine nozzle

Patent metadata

Field	Value
Publication number	US-2016146100-A1
Application number	US-201514709339-A
Country	US
Kind code	A1
Filing date	May 11, 2015
Priority date	Nov 21, 2014
Publication date	May 26, 2016
Grant date	—

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

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, and wherein the first sliding surface slides against a second sliding surface of the stationary vane.

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.

16 . A method for a turbine nozzle, comprising:
during a first condition, moving an actuation block coupled to a nozzle vane of the turbine nozzle from a first position to a second position to open the nozzle vane and move the nozzle vane against a shroud-side wall of the turbine nozzle; and during a second condition, moving the actuation block from the second position to a third position, the first position between the second position and the third position, and then back to the first position to close the nozzle vane and move the nozzle vane back against the shroud-side wall.

17 . The method of claim 16 , wherein the first condition includes when engine load is greater than a threshold load and wherein the second condition includes when engine load is less than the threshold load.

18 . The method of claim 16 , wherein the actuating block is shaped as a rhomboid.

19 . The method of claim 16 , wherein the actuation block is coupled to the nozzle vane through a pivotable yoke and rotatable shaft, the pivotable yoke surrounding two oppositely facing sides of the actuation block.

20 . The method of claim 16 , wherein moving the actuation block includes moving the actuation block in a circumferential direction relative to a central axis of a turbine wheel, the turbine nozzle surrounding the turbine wheel and sharing the central axis with the turbine wheel, and consequentially moving the yoke in the circumferential direction and an axial direction, the axial direction defined in a direction of the central axis.

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

• F05D2240/12

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

• F05D2210/30

  Flow characteristics · CPC title

• F02B37/24 Primary

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

• F01D5/141

  Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147) · CPC title