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US 2013/0280036 A1Published application
Axially-split radial turbine
AssigneeHoneywell International Inc.
InventorsDavid K. Jan, Christopher Zollars, Rajiv Rana, Tom Polakis, Ardeshir Riahi
Life of this patent
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Abstract
An axially-split radial turbine includes a forward rotor section and an aft rotor section being mechanically and abuttingly coupled to one another along an annular interface that resides within a plane generally orthogonal to a rotational axis of the axially-split radial turbine. The axially-split radial turbine can be provided as part of a gas turbine engine.
Claims20
An axially-split radial turbine comprising:
- a forward rotor section;
- and
- an aft rotor section,
- wherein the forward rotor section and the aft rotor section are mechanically and abuttingly coupled to one another along an annular interface that resides within a plane generally orthogonal to a rotational axis of the axially-split radial turbine.
1 more element
A gas turbine engine comprising:
- an axially-split radial turbine comprising:
- a forward rotor section;
- and
- an aft rotor section,
- wherein the forward rotor section and the aft rotor section are mechanically and abuttingly coupled to one another along an annular interface that resides within a plane generally orthogonal to a rotational axis of the axially-split radial turbine.
2 more elements
An axially-split radial turbine comprising:
- a forward rotor section;
- an aft rotor section, wherein the forward rotor section and the aft rotor section are mechanically and abuttingly coupled to one another along an annular interface that resides within a plane generally orthogonal to a rotational axis of the axially-split radial turbine;
- an inner annular cavity fully defined within the axially-split radial turbine;
- and
- a tie shaft for abuttingly coupling the forward rotor section to the aft rotor section
- wherein the forward rotor section comprises a forward blade segment and a forward hub section metallurgically bonded together along a first bond line and wherein the aft rotor section comprises an aft blade segment and an aft hub section metallurgically bonded together along a second bond line,
- wherein when the forward rotor section and the aft rotor section are coupled to one another, the forward blade segment and the aft blade segment define a contiguous radial turbine blade, and
- wherein the forward hub section defines a first annular cavity groove and wherein the aft hub section defines a second annular cavity groove, wherein when the forward rotor section and the aft rotor section are coupled to one another, the first and second annular grooves define the inner annual cavity.
5 more elements
Dependencies are inferred from the claim text.