US 11,952,910 B2 · Additively manufactured radial turbine rotor with cooling manifolds

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.

Claims19

Dependent claims

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;
impingement jets circumferentially disposed around and extending through a rear surface of the turbine rotor;
a plurality of exit jets extending through the trailing edge of each blade of the plurality of blades;
and
a plurality of cooling manifolds disposed within the turbine rotor extending between the impingement jets and the plurality of exit jets.

4 more elements

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, and each of the plurality of blades having a suction side and a pressure side, wherein 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 wherein 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;
and
a plurality of exit jets extending from the plurality of cooling manifolds and extending through the trailing edge of each blade of the plurality of blades;
a housing partially surrounding the turbine rotor;
a shaft mounted within the housing, the shaft comprising:
a seal between a bearing and a rear surface of the turbine rotor;
and
a cooling gap defined by the housing and the rear surface of the turbine rotor.

9 more elements

Dependencies are inferred from the claim text.

Additively manufactured radial turbine rotor with cooling manifolds

Life of this patent

Additively manufactured radial turbine rotor with cooling manifolds

Life of this patent

Abstract

Claims19