Additively manufactured radial turbine rotor with cooling manifolds

Patent metadata

Field	Value
Publication number	US-11680487-B2
Application number	US-202117453804-A
Country	US
Kind code	B2
Filing date	Nov 5, 2021
Priority date	Nov 5, 2021
Publication date	Jun 20, 2023
Grant date	Jun 20, 2023

Abstract

A turbine rotor includes a base and a plurality of blades. A central nose is radially inward of the blades and defines an axis of rotation. A plurality of cooling manifolds is disposed within the turbine rotor and includes impingement cooling jets extending through a rear surface of the turbine rotor. An internal cooling manifold extends radially inward of the impingement cooling jets and extends between the base and the rear surface of the turbine rotor. A central nose cooling manifold extends into the central nose and is fluidically connected to the internal cooling manifold. A base cooling manifold is fluidically connected to the central nose manifold and extends radially outward from the central nose cooling manifold. A blade cooling manifold is fluidically connected to the base cooling manifold and extends within the blade. Trailing edge jets extend from the blade cooling manifold and through the trailing edge of blades.

First claim

The invention claimed is:

1. A turbine rotor of a radial flow turbine, the turbine rotor comprising:
a base;
a plurality of blades circumferentially spaced about an axis of rotation and extending from the base, each of the plurality of blades extending radially outward from the base to a tip and chordwise from a leading edge to a trailing edge, each of the plurality of blades having a suction side and a pressure side;
a central nose radially inward of the plurality of blades, wherein the central nose defines the axis of rotation; and
a plurality of cooling manifolds disposed within the turbine rotor, wherein the plurality of cooling manifolds comprises:
impingement jets circumferentially disposed around and extending through a rear surface of the turbine rotor;
an internal manifold extending radially inward of the impingement jets and extending between the base and the rear surface of the turbine rotor;
a central nose manifold extending into the central nose, and fluidically connected to the internal manifold;
a base manifold fluidically connected to the central nose manifold and extending radially outwardly from the central nose manifold along the base adjacent the suction side of each blade;
a blade manifold fluidically connected to the base manifold extending within each blade from the base to the tip of each blade and extending from the leading edge toward the trailing edge of each blade; and
a plurality of exit jets extending from the blade manifold and through the trailing edge of each blade of the plurality of blades.

2. The turbine rotor of claim 1 , wherein the internal manifold comprises:
a primary cooling channel fluidically connected to the impingement jets, extending radially inward from the impingement jets between the base and rear surface of the turbine rotor, and extending along the suction side of each blade of the plurality of blades;
a secondary cooling channel fluidically connected to the impingement jets and extending radially inward the impingement jets between the base and the rear surface of the turbine rotor; and
a tertiary cooling channel fluidically connected to the impingement jets and extending radially inward the impingement cooling jets between the base and the rear surface of the turbine rotor,
wherein the primary cooling channel, the secondary cooling channel, and the tertiary cooling channel combine to form a main cooling channel at a radially inward position before the central nose manifold.

3. The turbine rotor of claim 2 , wherein each of the plurality of cooling manifolds comprises a cooling void interrupted by a plurality of columns extending axially within the primary cooling channel, the secondary cooling channel, and the tertiary cooling channel.

4. The turbine rotor of claim 3 , wherein each of the cooling manifolds comprises a cooling void interrupted by a plurality of columns extending circumferentially within the base manifold and in the blade manifold.

5. The turbine rotor of claim 4 , further comprising:
a plurality of guide passages fluidically connected between the base manifold and the blade manifold, wherein the plurality of guide passages extends from the base manifold to the blade manifold, and wherein each of the plurality of guide passages is angled from the base manifold towards the suction side of each blade, the leading edge of each blade, and the tip of each blade.

6. The turbine rotor of claim 5 , further comprising:
a first support rib extending radially between the primary cooling channel and the secondary cooling channel until the primary cooling channel and the secondary cooling channel meet at the main cooling channel;
a second support rib extending radially between the secondary cooling channel and the tertiary cooling channel until the secondary cooling channel and the tertiary cooling channel meet at the main cooling channel; and
a third support rib extending radially along the tertiary cooling channel opposite the second support rib until the tertiary cooling channel joins the main cooling channel.

7. The turbine rotor of claim 6 , wherein the turbine rotor is additively manufactured.

8. A method of making the turbine rotor of claim 1 , wherein the method comprises:
forming the turbine rotor via layer-by-layer additive manufacturing.

9. The method of claim 8 , wherein the turbine rotor is installed into a turbine module that comprises:
a housing surrounding the turbine rotor, wherein the housing comprises a working fluid inlet, a volute, and a working fluid outlet, wherein the working fluid inlet, the volute, and the working fluid outlet are fluidically connected;
a plurality of guide vanes configured to receive the working fluid from the volute and guide the working fluid to the turbine rotor;
a shaft extending through the housing and mechanically coupled to the turbine rotor;
a bearing that aligns the shaft; and
a seal installed on the shaft between the bearing and the rear surface of the turbine rotor.

10. A turbine module comprising:
a turbine rotor, wherein the turbine rotor comprises:
a base;
a plurality of blades circumferentially spaced about an axis of rotation and extending from the base, each of the plurality of blades extending radially outward from the base to a tip and chordwise from a leading edge to a trailing edge, each of the plurality of blades having a suction side and a pressure side, the base and each of the plurality of blades curve such that radially outward portions of the base and the plurality of blades extend more in a radial direction than in an axial direction, and radially central portions of the base and the plurality of blades extend similarly in the radial direction and the axial direction;
a central nose radially inward of the plurality of blades, wherein the central nose defines the axis of rotation;
a plurality of cooling manifolds disposed within the turbine rotor, wherein the plurality of cooling manifolds comprises:
impingement jets circumferentially disposed around and extending through a rear surface of the turbine rotor;
an internal manifold extending radially inward of the impingement jets and extending between the base and the rear surface of the turbine rotor;
a central nose manifold extending into the central nose and fluidically connected to the internal manifold;
a base manifold fluidically connected to the central nose manifold and extending radially outwardly from the central nose manifold along the base adjacent the suction side of each blade;
a blade manifold fluidically connected to the base manifold extending within each blade from the base to the tip of each blade and extending from the leading edge toward the trailing edge of each blade; and
a plurality of exit jets extending from the blade manifold and through the trailing edge of each blade of the plurality of blades; and

a housing surrounding the turbine rotor, wherein the housing comprises:
a shaft mounted within the housing, wherein the housing and a rear surface of the turbine rotor define a cooling gap.

11. The turbine module of claim 10 , wherein the internal manifold is comprised of:
a primary cooling channel fluidically connected to the impingement jets and extending radially inward from the impingement jets between the base and rear surface of the turbine rotor and extending along the suction side of each blade of the plurality of blades, and at least one of:
a secondary cooling channel fluidically connected to the impingement jets and extending radially inward the impingement jets between the base and the rear surface of the turbine rotor; and
a tertiary cooling channel fluidically connected to the impingement jets and extending radially inward the imping

Assignees

• Hamilton Sundstrand Corp

Inventors

• Dai Zhongtao
• Ranjan Ram
• Dold Robert H

Classifications

• F05D2260/201

  by impingement of a fluid · CPC title

• B33Y80/00

  Products made by additive manufacturing · CPC title

• F01D5/046 Primary

  Heating, heat insulation or cooling means · CPC title

• F01D5/048

  Form or construction · CPC title

• F05D2240/24

  for turbines · CPC title