Turbine vane structure

Patent · Tue Aug 19 00:00:00 EDT 1980

OSTI ID:863637

Irwin, John A ^[1]

---

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

Related Subjects

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