Robert C Tyler

US Patent:

6431850, Aug 13, 2002

Filed:

Aug 11, 2000

Appl. No.:

09/637433

Inventors:

Charles Richard Evans - Cincinnati OH
Robert Paul Tyler - Harrison OH

Assignee:

General Electric Company - Schenectady NY

International Classification:

B29C 7044

US Classification:

425470, 425390, 425403, 425DIG 44

Abstract:

A flexible tool that fits over the pressure or concave side of a metallic airfoil that includes a lightweight material component for a gas turbine engine during the fabrication of the airfoil. The metallic fan airfoil includes pockets or cavities that have been machined into the airfoil in order to reduce the weight of the airfoil. The tool is a flexible body manufactured from sheets of composite material and includes an integral elastomeric seal. The tool is placed over the airfoil and forms a seal against the pressure side of the airfoil so that lightweight resin can be injected into the pockets and retained in position during curing. The flexible tool is formed by laying up thin sheets of composite material that includes fiber over a metallic master tool after partially cured elastomeric material is placed inside a marking corresponding to the airfoil perimeter. The metallic master tool also includes slot positions corresponding to preselected positions, that form integral projections which allow the flexible tool to be correctly assembled and sealed against the airfoil.

US Patent:

20170114649, Apr 27, 2017

Filed:

Oct 23, 2015

Appl. No.:

14/921023

Inventors:

- Schenectady NY, US
Mark Eugene Noe - West Chester OH, US
Mark Willard Marusko - Springboro OH, US
Paul Izon - Morrow OH, US
Robert Tyler - Harrison OH, US
Christopher Hasse - Kenwood OH, US

International Classification:

F01D 5/28
F01D 5/14

Abstract:

Methods for fabricating a component of a gas turbine engine are provided. In one embodiment, the method includes molding a CMC material to form a first portion of the gas turbine engine component, processing the first portion to form a first assembly, preparing the first assembly and a second portion of the gas turbine engine component for processing, and processing the first assembly and second portion to form a second assembly. In another embodiment, the method includes processing a first plurality of CMC plies to form a first assembly; positioning the first assembly and a second plurality of CMC plies on a tool for processing, the first assembly defining a first plane, the second plurality of plies defining a second plane, wherein the second plane is perpendicular to the first plane; and processing the first assembly and the second plurality of plies to form a second assembly.