Title:
GAS TURBINE ENGINE AIRFOIL
Document Type and Number:
WIPO Patent Application WO/2015/175058
Kind Code:
A3
Abstract:
A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a trailing edge angle and span position that defines a curve with a non-negative slope from 0% span to 20% span corresponding to a non-decreasing trailing edge angle.
Inventors:
GALLAGHER EDWARD J (US)
BRILLIANT LISA I (US)
STRACCIA JOSEPH C (US)
STEPHENS MARK A (US)
BALAMUCKI STANLEY J (US)
HUDON KATE (US)
BRILLIANT LISA I (US)
STRACCIA JOSEPH C (US)
STEPHENS MARK A (US)
BALAMUCKI STANLEY J (US)
HUDON KATE (US)
Application Number:
PCT/US2015/016135
Publication Date:
January 14, 2016
Filing Date:
February 17, 2015
Export Citation:
Assignee:
UNITED TECHNOLOGIES CORP (US)
International Classes:
F01D5/14; F04D29/38
Foreign References:
| US20110081252A1 | 2011-04-07 | |||
| US20130340406A1 | 2013-12-26 | |||
| US20130089415A1 | 2013-04-11 | |||
| US20130189117A1 | 2013-07-25 | |||
| US20120237344A1 | 2012-09-20 |
Other References:
See also references of EP 3108121A4
Attorney, Agent or Firm:
GOTTSCHALK, William S. (GASKEY & OLDS P.C.,400 West Maple Road, Suite 35, Birmingham Michigan, US)
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