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US 2010/0166551 A1Published application
Hybrid turbomachinery component for a gas turbine engine
AssigneeROLLS-ROYCE plc
InventorAdam J. Morrison
Life of this patent
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Abstract
The present invention provides a hybrid turbomachinery component for use in a gas turbine engine. The hybrid turbomachinery component may be operative to direct the working fluid of the gas turbine engine and/or addi energy to the working fluid and/or extract energy from the working fluid. One or more portions of the hybrid turbomachinery component are made from one material, and other portions of the hybrid turbomachinery component are made from another material.
Claims20
A turbomachinery component for a gas turbine engine, comprising:
- an airfoil portion formed of a first material;
- an attachment portion extending from a root of the airfoil portion and structured to secure the airfoil portion to the gas turbine engine;
- a retention feature disposed adjacent to one of said attachment portion and said airfoil portion;
- and
- a flowpath structure molded around the retention feature and formed of a second material different than the first material, wherein the flowpath structure is retained by the retention feature.
2 more elements
A gas turbine engine, comprising:
- one of a fan and a compressor having a hybrid turbomachinery component, wherein the hybrid turbomachinery component includes:
- an airfoil portion formed of a first material;
- an attachment portion extending from a root of the airfoil portion, wherein the attachment portion is operative to secure the airfoil portion to the gas turbine engine;
- a retention feature adjacent to one of said attachment portion and said airfoil portion;
- and
- a flowpath structure molded to the retention feature and formed of a second material different than the first material, wherein the flowpath structure is retained by the retention feature.
3 more elements
A method comprising:
- forming an airfoil portion from a first material;
- forming an attachment portion extending from a root of the airfoil portion, wherein the attachment portion is structured to secure the hybrid turbomachinery component to the gas turbine engine;
- forming a retention feature adjacent to one of the attachment portion and the airfoil portion;
- and
- insert molding a flowpath structure around the retention feature using a second material different than the first material, wherein the flowpath structure is retained by the retention feature.
2 more elements
Dependencies are inferred from the claim text.