Mini-disk for gas turbine engine
AssigneeUnited Technologies Corporation
InventorsRaymond S. Hummel, Julian Partyka
Life of this patent
Estimating the term…
Abstract
Mini-disks of gas turbine engines are provided having an axially extending portion extending axially with respect to an axis of the engine, the axially extending portion configured to engage with a hub arm of a compressor of the engine, a radially extending portion extends radially with respect to the axis, the radially extending portion configured to engage with an attachment of a turbine disk of the gas turbine engine, an intermediate portion extending between the axially extending portion and the radially extending portion, and at least one mini-disk connector configured to engage with a portion of the turbine disk of the gas turbine engine to prevent radial movement of the mini-disk during operation.
Claims20
A mini-disk of a gas turbine engine having an axis comprising:
- an axially extending portion extending axially with respect to the axis of the gas turbine engine, the axially extending portion configured to engage with a hub arm of a compressor of the gas turbine engine;
- a radially extending portion extending radially with respect to the axis of the gas turbine engine, the radially extending portion configured to engage with an attachment of a turbine disk of the gas turbine engine;
- an intermediate portion extending between the axially extending portion and the radially extending portion;
- and
- at least one mini-disk connector configured to engage with a portion of the turbine disk of the gas turbine engine to prevent radial movement of the mini-disk during operation.
A gas turbine engine having an axis comprising:
- a turbine disk having an attachment and at least one disk connector;
- a compressor hub arm axially forward of the turbine disk;
- and
- a mini-disk configured between the turbine disk and the compressor hub arm, the mini-disk comprising:
- an axially extending portion extending axially with respect to the axis of the gas turbine engine, the axially extending portion configured to engage with the compressor hub arm;
- a radially extending portion extending radially with respect to the axis of the gas turbine engine, the radially extending portion configured to engage with the attachment of the turbine disk;
- an intermediate portion extending between the axially extending portion and the radially extending portion;
- and
- at least one mini-disk connector configured to engage with the at least one disk connector to prevent radial movement of the mini-disk during operation.
Dependencies are inferred from the claim text.