Invention Grant
- Patent Title: Gas turbine engine airfoil cooling configuration with pressure gradient separators
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Application No.: US14632485Application Date: 2015-02-26
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Publication No.: US10385699B2Publication Date: 2019-08-20
- Inventor: San Quach , Ryan Alan Waite , Christopher King , Steven Bruce Gautschi
- Applicant: United Technologies Corporation
- Applicant Address: US CT Farmington
- Assignee: United Technologies Corporation
- Current Assignee: United Technologies Corporation
- Current Assignee Address: US CT Farmington
- Agency: Carlson, Gaskey & Olds, P.C.
- Main IPC: F01D5/14
- IPC: F01D5/14 ; F01D5/18 ; F01D9/04 ; F23R3/00 ; F01D11/08 ; F01D25/30

Abstract:
An airfoil for a gas turbine engine includes an airfoil including spaced apart pressure and suction side walls joined at leading and trailing edges to provide an exterior airfoil surface that extends in a radial direction from a platform to a tip. A cavity is provided between the pressure and suction side walls near the trailing edge. The cavity includes an interior region bounded by first and second exit regions arranged at angle relative to one another. The first and second exit regions are respectively in low and high pressure regions relative to one another. First and second pedestal groups respectively are arranged at the first and second exit regions. The second pedestal group has first and second pedestals each terminating in an end. The ends of the second pedestals extend beyond the ends of first pedestals.
Public/Granted literature
- US20160251968A1 GAS TURBINE ENGINE AIRFOIL COOLING CONFIGURATION WITH PRESSURE GRADIENT SEPARATORS Public/Granted day:2016-09-01
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