# US 2010/0166551 A1 · Hybrid turbomachinery component for a gas turbine engine > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2010/0166551 A1 - Document ID: US20100166551A1 - Status: Published application - Kind: A1 - Application number: 12/639,576 - Filed: 2009-12-16 - Published: 2010-07-01 - Earliest claimed: 2008-12-29 - Assignees: ROLLS-ROYCE plc - Inventors: Adam J. Morrison - Web page: https://patentgrep.com/patent/US20100166551A1 ## CPC - F23R 3/007: {constructed mainly of ceramic components} - F23M 5/04: Supports for linings - F23M 2900/05004: Special materials for walls or lining - Y02E 20/14: Combined heat and power generation [CHP] - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - Y10T 29/49245: Vane type or other rotary, e.g., fan - Y10T 29/49321: Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member - Y10T 29/49325: Shaping integrally bladed rotor - F23R: GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS (fluidised bed combustion apparatus specially adapted for operation at superatmospheric pressures F23C10/16) - F23M: CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR - Y02E: REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION - Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION ## 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. ## Claims ### Claim 1 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. ### Claim 2 (depends on 1) The turbomachinery component of claim 1, wherein said airfoil portion and said attachment portion are formed as a unitary structure from the first material. ### Claim 3 (depends on 1) The turbomachinery component of claim 1, wherein the turbomachinery component is structured as a blade, and wherein said flowpath structure is a blade platform defining in part a flowpath in said gas turbine engine. ### Claim 4 (depends on 3) The turbomachinery component of claim 3, wherein said attachment portion is structured to secure said blade to a rotating disk in one of a fan and a compressor of the gas turbine engine. ### Claim 5 (depends on 4) The turbomachinery component of claim 4, wherein the rotating disk includes a slot, and wherein said attachment portion includes a dovetail structured to engage and be radially retained by the slot in the rotating disk. ### Claim 6 (depends on 3) The turbomachinery component of claim 3, wherein said retention feature extends substantially perpendicular from said one of said attachment portion and said airfoil portion. ### Claim 7 (depends on 1) The turbomachinery component of claim 1, wherein said first material is a metal alloy and said second material is a composite material. ### Claim 8 (depends on 1) The turbomachinery component of claim 1, wherein said flowpath structure encapsulates said retention feature. ### Claim 9 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. ### Claim 10 (depends on 9) The gas turbine engine of claim 9, wherein said airfoil portion and said attachment portion are formed as a unitary structure from the first material. ### Claim 11 (depends on 9) The gas turbine engine of claim 9, wherein the hybrid turbomachinery component is a blade, and wherein said flowpath structure is a blade platform defining in part a flowpath in said gas turbine engine. ### Claim 12 (depends on 11) The gas turbine engine of claim 11, wherein said attachment portion is structured to secure said blade to a rotable disk in one of said fan and said compressor. ### Claim 13 (depends on 12) The gas turbine engine of claim 12, wherein said rotatable disk has a slot, and wherein said attachment portion includes a dovetail structured to engage and be radially retained by said slot in the rotating disk. ### Claim 14 (depends on 11) The gas turbine engine of claim 11, wherein said retention feature extends substantially perpendicular from said one of said attachment portion and said airfoil portion. ### Claim 15 (depends on 9) The gas turbine engine of claim 9, wherein said first material is a metal alloy and said second material is a composite material. ### Claim 16 (depends on 9) The gas turbine engine of claim 9, wherein said flowpath structure encapsulates said retention feature. ### Claim 17 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. ### Claim 18 (depends on 17) The method of claim 17, wherein the first material is a metal alloy and the second material is a composite material. ### Claim 19 (depends on 17) The method of claim 17, wherein the airfoil portion and the attachment portion are forged as a unitary structure from the first material. ### Claim 20 (depends on 17) The method of claim 17, wherein the airfoil portion and the attachment portion are formed as a unitary structure by twisting plate stock of the first material.