Invention Grant
- Patent Title: Turbine engine compressor blade
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Application No.: US15018126Application Date: 2016-02-08
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Publication No.: US10221859B2Publication Date: 2019-03-05
- Inventor: Curtis William Moeckel , Peter John Wood , Matthew Ford Adam , Eric Andrew Falk , Mark Joseph Stecher
- Applicant: General Electric Company
- Applicant Address: US NY Schenectady
- Assignee: General Electric Company
- Current Assignee: General Electric Company
- Current Assignee Address: US NY Schenectady
- Agency: General Electric Company
- Agent Pamela Kachur
- Main IPC: F04D29/32
- IPC: F04D29/32

Abstract:
An airfoil for a compressor blade of a gas turbine engine has a chord between a leading edge and a trailing edge and a span between a root and a tip. The airfoil can further include a reduction in local chord from about 75% span to the tip for about a 5% reduction in local solidity. The airfoil can have decreasing sweep angles for the leading edge and the trailing edge from 50% span to the tip and can have decreasing leading and trailing edge dihedral angles from 50% span to the tip.
Public/Granted literature
- US20170227016A1 TURBINE ENGINE COMPRESSOR BLADE Public/Granted day:2017-08-10
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