Back to results
US 10,844,734 B2Granted
Ceramic turbine volute
AssigneeIcr Turbine Engine Corporation
InventorMatthew Stephen Baldwin
Life of this patent
Estimating the term…
Abstract
A gas turbine and nozzle system is provided that includes a radial inflow turbine rotor and a volute providing a flow path to deliver a pressurized gas to a circumference of the radial turbine rotor. The volute incorporates a shape which substantially conforms to a radial turbine shroud contour. The volute includes at least first and second parts. A mating surface between the first and second parts is substantially aligned with a direction of pressurized gas flow in the volute.
Claims20
A gas turbine and nozzle system, comprising:
- a radial inflow turbine rotor;
- a radial turbine shroud;
- and
- a volute comprising a shape conforming to a contour of the radial turbine shroud, the volute comprising at least first and second parts clamped between rings,
- wherein the first and second parts comprise a ceramic material,
- wherein the ceramic material has a thermal conductivity higher than first and second thermal barriers,
- wherein the first and second parts and the first and second thermal barriers are stacked in an axial plane and share a first turbine axis,
- wherein a mating surface between the first and second parts is aligned with a direction of an up-stream pressurized gas flow in the volute,
- wherein the first and second parts operatively engage each other along a plane which is perpendicular to the first turbine axis,
- wherein the volute provides a flow path to deliver a pressurized gas to a circumference of the radial turbine rotor.
7 more elements
A gas turbine and nozzle system, comprising:
- a radial inflow turbine rotor;
- a radial turbine shroud;
- a volute comprising a shape conforming to a contour of the radial turbine shroud, wherein the volute comprises at least first and second parts clamped between rings,
- wherein the first and second parts comprise a ceramic material,
- wherein the ceramic material has a thermal conductivity higher than first and second thermal barriers,
- wherein the first and second parts and the first and second thermal barriers are stacked in an axial plane and share a first turbine axis,
- wherein a mating surface between the first and second parts is aligned with a direction of an up-stream pressurized gas flow in the volute,
- wherein the first and second parts operatively engage each other along a plane which is perpendicular to the first turbine axis,
- wherein the volute provides a flow path to deliver a pressurized gas to a circumference of the radial turbine rotor,
- wherein the first and second thermal barriers correspond respectively to the first and second parts of the volute, and
- wherein the first thermal barrier is positioned between the first part and a first bearing core and the second thermal barrier is positioned between the second part and a second bearing core.
8 more elements
A method, comprising:
- inserting a radial inflow turbine rotor through a turbine exit end of a pressure bearing housing and through a first part of a volute;
- and thereafter engaging the first part of the volute with a second part of the volute to enclose the radial inflow turbine rotor between the first and second parts of the volute,
- wherein the volute comprises a shape conforming to a contour of a radial turbine shroud,
- wherein the first and second parts are clamped between rings,
- wherein the first and second parts comprise a ceramic material,
- wherein the ceramic material has a thermal conductivity higher than first and second thermal barriers,
- wherein the first and second parts and the first and second thermal barriers are stacked in an axial plane and share a first turbine axis,
- wherein a mating surface between the first and second parts is aligned with a direction of an up-stream pressurized gas flow in the volute,
- wherein the first and second parts operatively engage each other along a plane which is perpendicular to the first turbine axis,
- wherein the volute provides a flow path to deliver a pressurized gas to a circumference of the radial turbine rotor.
7 more elements
Dependencies are inferred from the claim text.