Turbine row with diffusive geometry

Patent metadata

Field	Value
Publication number	US-2023417143-A1
Application number	US-202318215016-A
Country	US
Kind code	A1
Filing date	Jun 27, 2023
Priority date	Jun 27, 2022
Publication date	Dec 28, 2023
Grant date	—

Abstract

A turbine row for an axial or mixed-flow fluid machine may include an airfoil, having a leading edge, a trailing edge, a pressure surface and a suction surface. The turbine row may further include two endwalls, extending from upstream of the airfoil leading edge to downstream of the airfoil trailing edge. The endwalls may define an inlet upstream of the leading edge of the airfoil and an outlet downstream of the airfoil. The endwalls have a contoured geometry which provides an increase in channel height from the inlet to the outlet and guarantees a throat area larger than the area of the inlet.

First claim

What is claimed is:

1 . A turbine row for an axial or mixed-flow fluid machine, comprising
an airfoil, having a leading edge, a trailing edge, a pressure surface and a suction surface; and two endwalls, extending from upstream of the airfoil leading edge to downstream of the airfoil trailing edge, wherein the endwalls define an inlet upstream of the leading edge of the airfoil and an outlet downstream of the airfoil, wherein the endwalls have a contoured geometry which provides an increase in channel height from the inlet to the outlet and guarantees a throat area larger than the area of the inlet.

2 . The turbine row of claim 1 , wherein the channel height at the throat is larger than the channel height at the inlet.

3 . The turbine row of claim 1 , wherein the airfoil can provide turning to the flow for any inlet Mach number, both in at subsonic and supersonic operation, without creating a normal shock upstream of the leading edge of the airfoil.

4 . The turbine row of claim 1 , wherein the throat to area ratio is at least 1.4.

5 . The turbine row of claim 1 , wherein the endwalls are smooth contours with an angle that varies along a direction of acceleration.

6 . The turbine row of claim 1 , wherein the channel height increase is distributed along a direction of acceleration between a region upstream of the airfoil leading edge (LE), the region along the airfoil itself and a region downstream of the airfoil trailing edge (TE).

7 . The turbine row of claim 1 , further including an extension to the airfoil positioned at least one of the endwalls adjacent to the airfoil.

8 . The turbine row of claim 9 , wherein the extension is upstream of the airfoil leading edge.

9 . The turbine row of claim 9 , wherein the extension is downstream of the airfoil trailing edge.

10 . The turbine row of claim 1 , wherein endwalls are contoured such that space between the endwalls is symmetric with respect to a passage mean radius.

11 . The turbine row of claim 1 , wherein endwalls are contoured such that space between the endwalls is not symmetric with respect to a passage mean radius.

12 . A turbine row of claim 1 , wherein a first one of the endwalls is a hub endwall and a second one of the endwalls is a shroud endwall, wherein the hub endwall does not have a change in radius, and the entire channel height variation is created by the radius increase in the shroud enwall.

13 . A turbine row of claim 1 , wherein a first one of the endwalls is a hub endwall and a second one of the endwalls is a shroud endwall, wherein the shroud endwall does not have any change in radius, and the entire channel height variation is created by the radius decrease in the hub endwall.

14 . A turbine row of claim 1 , wherein the endwalls are axisymmetric.

15 . A turbine row of claim 1 , wherein the endwalls are non-axisymmetric.

16 . A turbine row of claim 1 , wherein a chord of the airfoil has a first axial length proximate to one of the endwalls and a second axial length proximate to the mean passage radius, wherein the first axial length is greater than the second axial length.

17 . A turbine row of claim 1 , wherein a chord of the airfoil has a first axial length proximate to one of the endwalls and a second axial length proximate to the mean passage radius wherein the first axial length is less than the second axial length.

18 . A turbine row of claim 1 , wherein the airfoil of the turbine row is stationary and does not rotate about a centerline of the turbine row.

19 . The turbine row of claim 1 , wherein the airfoil of the turbine row rotates about a centerline of the turbine row.

20 . The turbine row of claim 1 , wherein the turbine row is configured for a gas turbine engine, power plant, propulsive system, or power extraction system.

21 . The turbine row of claim 1 , wherein the airfoil is coupled to a first one of the endwalls but not a second one of the endwalls.

22 . The blade row of claim 1 , wherein the airfoil is coupled to both endwalls.

Assignees

• Purdue Research Foundation

Inventors

• Paniagua-Perez Guillermo
• Martinez Sergio Grasa

Classifications

• F01D5/141 Primary

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

• F05D2240/302

  characteristics related to shock waves, transonic or supersonic flow · CPC title

• F01D5/145

  Means for influencing boundary layers or secondary circulations (for compressors F04D29/68) · CPC title

• F01D9/041

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