Asymmetrically shaped trailing edge cooling holes

A turbine airfoil (12) includes pressure and suction sidewalls (42, 44) extending along a span (S) from a base (34) to a tip (36). Spanwise spaced apart trailing edge cooling holes (30) in pressure sidewall (42) end at corresponding spanwise spaced apart trailing edge cooling slots (66) extending ch...

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Bibliographic Details
Main Authors DURSTOCK DANIEL LEE, BERGHOLZ ROBERT FREDERICK
Format Patent
LanguageEnglish
Published 01.04.2015
Subjects
BLASTING
ENGINE PLANTS IN GENERAL
HEATING
LIGHTING
MACHINES OR ENGINES IN GENERAL
MECHANICAL ENGINEERING
NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES
STEAM ENGINES
WEAPONS
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Summary:A turbine airfoil (12) includes pressure and suction sidewalls (42, 44) extending along a span (S) from a base (34) to a tip (36). Spanwise spaced apart trailing edge cooling holes (30) in pressure sidewall (42) end at corresponding spanwise spaced apart trailing edge cooling slots (66) extending chordally substantially to trailing edge (TE). Each cooling hole (30) includes an asymmetric flow cross section (74) through one or more asymmetric intermediate sections (101) leading into slot (66). Flow cross section (74) is asymmetric with respect to a mid-plane (75) extending axially and spanwise through intermediate sections (101). Different trailing edge cooling holes (30) may include different asymmetric flow cross sections (74). Lands (50) may extend between the cooling slots (66). A raised floor (88) may extend away from at least one of pressure or suction sidewalls (42, 44) at least partially through one or more asymmetric intermediate sections (101) and optionally at least partially through cooling slot (66). Raised floor (88) may include up and down ramps (90, 94) and a flat transition section (92) between ramps (90, 94).
Bibliography:Application Number: CN201380024123