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Engine Component
Abstract: An engine component (80) for a gas turbine engine (10) includes a film-cooled substrate (82) having a hot surface (84) facing hot combustion gas and a cooling surface (86) facing a cooling fluid flow. The substrate (82) includes one or more film holes (90) that have a passage (96) with an inlet (92) and an outlet (94), where the passage (96) includes portions (98, 100) that are angled relative to each other. FIG.5
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Notices, Deadlines & Correspondence
Notices, Deadlines & Correspondence
Patent Information
Application #
Filing Date
24 February 2016
Publication Number
35/2016
Publication Type
INA
Invention Field
MECHANICAL ENGINEERING
Status
Email
bpo.mail@ge.com
Parent Application
Applicants
GENERAL ELECTRIC COMPANY
1 River Road
Schenectady, New York 12345
USA
Inventors
1. BUNKER, Ronald Scott
GE Aviation
9075 Centre Pointe Drive
West Chester, OH 45069
USA
2. BUCK, Frederick Alan
9075 Centre Pointe Drive
West Chester, OH 45069
USA
Specification
SOFT COPY ATTACHED IN PDF
Documents
Application Documents
| # | Name | Date |
|---|---|---|
| 1 | Power of Attorney [24-02-2016(online)].pdf | 2016-02-24 |
| 2 | Form 5 [24-02-2016(online)].pdf | 2016-02-24 |
| 3 | Form 3 [24-02-2016(online)].pdf | 2016-02-24 |
| 4 | Drawing [24-02-2016(online)].pdf | 2016-02-24 |
| 5 | Description(Complete) [24-02-2016(online)].pdf | 2016-02-24 |
| 6 | absatract 201644006328.jpg | 2016-07-12 |