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Title: Turbine vane structure

Abstract

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 edgemore » 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.« less

Inventors:
 [1]
  1. Greenwood, IN
Publication Date:
Research Org.:
Energy Research Development Administration
OSTI Identifier:
863637
Patent Number(s):
US 4218178
Application Number:
05/892,392
Assignee:
General Motors Corporation (Detroit, MI)
Resource Type:
Patent
Country of Publication:
United States
Language:
English
Subject:
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/

Citation Formats

Irwin, John A. Turbine vane structure. United States: N. p., 1980. Web.
Irwin, John A. Turbine vane structure. United States.
Irwin, John A. Tue . "Turbine vane structure". United States. https://www.osti.gov/servlets/purl/863637.
@article{osti_863637,
title = {Turbine vane structure},
author = {Irwin, John A},
abstractNote = {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.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {1980},
month = {8}
}

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