Turbine vane structure

Patent · Tue Aug 19 04:00:00 EDT 1980

OSTI ID:863637

Irwin, John A ^[1]

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1. Greenwood, IN

A liquid cooled stator blade assembly for a gas turbine engine includes an outer shroud having a pair of liquid inlets and a pair of liquid outlets supplied through a header and wherein means including tubes support the header radially outwardly of the shroud and also couple the header with the pair of liquid inlets and outlets. A pair of turbine vanes extend radially between the shroud and a vane platform to define a gas turbine motive fluid passage therebetween; and each of the vanes is cooled by an internal body casting of super alloy material with a grooved layer of highly heat conductive material that includes spaced apart flat surface trailing edges in alignment with a flat trailing edge of the casting joined to wall segments of the liner which are juxtaposed with respect to the internal casting to form an array of parallel liquid inlet passages on one side of the vane and a second plurality of parallel liquid return passages on the opposite side of the vane; and a superalloy heat and wear resistant imperforate skin covers the outer surface of the composite blade including the internal casting and the heat conductive layer; a separate trailing edge section includes an internal casting and an outer skin butt connected to the end surfaces of the internal casting and the heat conductive layer to form an easily assembled liquid cooled trailing edge section in the turbine vane.

• Research Organization: Energy Research Development Administration
• Assignee: General Motors Corporation (Detroit, MI)
• Patent Number(s): US 4218178
• Application Number: 05/892,392
• OSTI ID: 863637
• Country of Publication: United States
• Language: English

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/415/416/
alignment
alloy
alloy heat
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apart
array
assembled
assembly
blade
butt
casting
composite
conductive
conductive layer
conductive material
connected
cooled
couple
covers
define
easily
easily assembled
edge
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engine
extend
extend radially
flat
flat surface
fluid
fluid passage
form
gas
gas turbine
grooved
header
heat
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highly
imperforate
including
inlet
inlet passage
inlet passages
inlets
internal
joined
juxtaposed
layer
liner
liquid
liquid cooled
liquid inlet
liquid inlets
material
means
means including
motive
motive fluid
opposite
outer
outer shroud
outer surface
outlets
outwardly
pair
parallel
passage
passages
platform
plurality
radially
radially outward
radially outwardly
resistant
respect
return
section
segments
separate
shroud
spaced
spaced apart
stator
structure
super
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superalloy
supplied
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surface
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therebetween
trailing
trailing edge
tubes
tubes support
turbine
turbine engine
turbine vane
vane
vanes
vanes extend
wall
wall segment
wall segments
wear
wear resistant