U.S. patent number 3,644,059 [Application Number 05/043,838] was granted by the patent office on 1972-02-22 for cooled airfoil.
Invention is credited to John K. Bryan.
United States Patent |
3,644,059 |
Bryan |
February 22, 1972 |
COOLED AIRFOIL
Abstract
A transpiration-cooled turbine blade has a porous wall and may
have an internal strut extending spanwise of the blade and carrying
cooling air into the blade. A honeycomb material with the cells
extending generally from face-to-face of the blade is bonded to the
interior of the blade wall and to the strut, if present. If there
is no strut, the honeycomb extends from face-to-face, and has air
supply passages cut through the honeycomb extending spanwise of the
blade.
Inventors: |
Bryan; John K. (Glen Cove, L.
I., NY) |
Family
ID: |
21929152 |
Appl.
No.: |
05/043,838 |
Filed: |
June 5, 1970 |
Current U.S.
Class: |
416/97R; 416/96R;
29/889.721; 416/97A; 416/231R |
Current CPC
Class: |
F01D
5/183 (20130101); Y10T 29/49341 (20150115) |
Current International
Class: |
F01D
5/18 (20060101); F01d 005/18 () |
Field of
Search: |
;416/96-97,231,223 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Powell, Jr.; Everette A.
Claims
I claim:
1. A fluid-directing airfoil member for use in hot environments
comprising, in combination, an outer skin defining the airfoil
contour, the outer skin being of a porous material adapted for
transpiration cooling by flow of coolant outwardly through the
skin; an open-cell honeycomb structural material lining the outer
skin and bonded to the outer skin, with the cells of the honeycomb
open to the skin and extending inwardly from the skin to define
cooling fluid passages from the interior of the airfoil element to
the inner surface of the skin and providing a structural
reinforcement for the skin resisting displacement of the skin; and
means for conducting a cooling fluid through the interior of the
airfoil member into the honeycomb material for flow through the
said passages and skin.
2. A member as defined in claim 1 in which the last-recited means
includes a rigid hollow strut extending spanwise of the blade
bonded to the honeycomb material.
3. A member as defined in claim 1 in which the last-recited means
is formed by passages extending spanwise of the blade cutting
through the cell walls of the honeycomb material.
4. A member as defined in claim 1 in which the last-recited means
includes means defining at least one passage extending spanwise of
the blade and includes apertures through the cell walls of the
honeycomb material for distribution of the cooling fluid from cell
to cell.
5. A member as defined in claim 1 in which the last-recited means
includes metering restrictions adapted to proportion the flow of
cooling fluid to various areas of the outer skin in accordance with
external pressure and cooling requirements at such various
areas.
6. A hollow flow-directing airfoil member comprising, in
combination, a wall of controlled porosity adapted for
transpiration cooling effected by fluid flowing outward through the
wall, the member being of airfoil cross section with a
high-pressure face and a low-pressure face, a fluid distributing
and metering layer bonded to the inner surface of the wall at both
faces, and an internal strut adapted to support the wall against
deflection and to supply a cooling fluid to the wall, the internal
strut being a hollow structure extending spanwise of the airfoil
and defining at least one cooling fluid passage extending spanwise
of the airfoil, the said layer being bonded to the strut and being
composed of a honeycomb material with cells extending from the
strut to the interior surface of the wall, and fluid distributing
apertures in the strut connecting the said duct to the said
layer.
7. A member as defined in claim 6 including also apertures between
some of the honeycomb material cells for further distribution of
the fluid.
8. A fluid-directing airfoil member for use in hot environments
comprising, in combination, an outer skin defining the airfoil
contour, the outer skin being of a porous material adapted for
transpiration cooling; the skin defining an airfoil with a leading
edge, a trailing edge, and high- and low-pressure faces extending
from the leading edge to the trailing edge and enclosing the
interior of the blade; a reinforcing and fluid-distributing
structure within the airfoil comprising a structural honeycomb
extending between, and bonded to the interior of, the inside of the
skin of the faces, the honeycomb having open cells extending from
face to face of the blade; passages within the honeycomb material
extending spanwise of the airfoil being defined by voids in the
honeycomb material, the passages communicating with the cells of
the honeycomb material, so that a cooling fluid may be supplied
through the passages and thence through the cells of the honeycomb
to the interior of the outer skin.
9. A member as defined in claim 8 including also apertures between
some of the honeycomb material cells for further distribution of
the fluid.
Description
The invention herein described was made in the course of work under
a contract or subcontract thereunder with the Department of
Defense."
This patent application was filed under the provisions of 35 U.S.
Code Section 118 by General Motors Corporation, a corporation of
Delaware, which asserts ownership of the application by virtue of a
contract of employment of the inventor with General Motors
Corporation.
DESCRIPTION
My invention relates to improvements in hollow fluid directing
members for high-temperature turbomachines, such as vanes and
blades for gas turbines. It is particularly directed to improving
the cooling and providing adequate stiffening in blades in which
the wall is a thin laminate of porous material or is of other
material of a porous nature so that the blade may be cooled by
transpiration cooling; that is, by air or other cooling fluid which
flows through the walls of the blade and is discharged from
multifarious pores in the outer surface of the blade. The term
"blade" will be used here to refer to vanes and blades and other
analogous structures. My invention may apply to any such which
require cooling and which need to be strengthened or internally
reinforced and to have the distribution of cooling fluid
controlled, although the preferred embodiment is in a turbine
blade.
Considering a turbine blade, the amount of heat transfer to the
blade varies over the area of the blade wall. Also, external
pressures vary, being generally low on the convex surface of the
blade relative to the concave or high-pressure face. Economy of
cooling fluid and even cooling of the surface may be improved by
arrangements to control or meter the flow of fluid to the lower
pressure surfaces of the blade. The pressure of the cooling fluid
supplied to the blade must, of course, be greater than the maximum
pressure outside the blade for cooling fluid to flow through the
entire surface. Thus, it may be desirable to throttle or meter the
flow to some parts of the blade so as to reduce the pressure and
prevent undue and wasteful discharge of cooling fluid through the
areas exposed to lower pressure. Also, there is a tendency for the
pressure within the blade to balloon the airfoil and there may be
gas bending loads and buffeting forces on the blade from the motive
gas, and possibly other forces which tend to deflect the walls of
the blade or other flow-deflecting element.
My invention is directed to improvements in porous walled blades
such as to strengthen the wall and to improve the distribution of
cooling fluid to the wall. In the preferred embodiments of the
invention, the blade is an airfoil having walls formed of a
laminated porous metal sheet of the type described in U.S. Pat. No.
3,584,972 of Meginnis and Bratkovich.
The blade walls define a hollow interior which is filled with
material which distributes fluid to the blade walls, and
strengthens and stiffens the blade. Two forms are disclosed, in one
of which honeycomb material extends from face to face of the blade
between the inner surfaces of the walls, thus connecting the faces
together and providing a reinforcement within the blade. Spanwise
extending passages cut through the honeycomb material distribute
the cooling fluid spanwise of the blade, and it flows from these
passages through the cells of the honeycomb material to the blade
wall. In this structure the honeycomb serves to stiffen the blade
against bending loads, as well as other deflections or
ballooning.
In a further form of the invention, a greater degree of stiffness
is obtained by the use of a hollow strut of relatively heavy
section compared to the blade walls. In this case, the strut
provides the spanwise extending cooling air passages and delivers
the air to a layer of honeycomb between the strut and the blade
wall.
Of course, various structures embodying the principles of the
invention may be derived from these preferred embodiments,
described in detail in this specification.
The principal objects of my invention are to provide
transpiration-cooled turbine blades and vanes and other analogous
airfoil devices of improved strength and rigidity, which may be
readily fabricated, and which have superior structure for
distribution of the cooling air to various areas of the wall of the
airfoil.
The nature of my invention and its advantages will be more clearly
apparent to those skilled in the art from the succeeding detailed
description of preferred embodiments of the invention and the
accompanying drawings thereof.
FIG. 1 is an elevation view of a turbine blade.
FIG. 2 is a cross section of the same taken on the plane indicated
by the line 2--2 in FIG. 1.
FIG. 3 is a considerably enlarged view of a fragment of FIG. 2.
FIG. 4 is a fragmentary sectional view taken on a curved surface
indicated generally by the line 4--4 in FIG. 3.
FIG. 5 is a sectional view, taken on a plane similar to that of
FIG. 2, of a second form of blade structure.
FIG. 1 illustrates what may be regarded as a typical turbine blade
except for structure not shown in FIG. 1. The blade 6 includes a
fluid-directing airfoil 7 and a base 8 by which it is mounted on a
turbine rotor. The base is an integral cast structure comprising a
platform 10, a stalk 11, and a root 12. The airfoil 7 is a formed
structure of sheet metal of controlled porosity for diffusion of
cooling air through the walls of the blade for transpiration
cooling. While various types of porous material may be employed in
the blade wall, the preferred material is that described and
claimed in the Bratkovich et al., patent referred to above. The
airfoil may be bicast or otherwise secured to the base 8. The
airfoil 7 may have any suitable shape but, as illustrated more
clearly in FIG. 2, is of cambered airfoil cross section having a
convex or low-pressure face 14 and a concave or high-pressure face
15, these extending from a rounded leading edge 16 to a
sharp-trailing edge 18.
Cooling air may be admitted to the interior of the airfoil 7
through an opening 19 in the blade base and the free end or tip of
the blade is closed by a cap 20 or other suitable closure. The air
introduced into the blade escapes through numerous small pores 22
distributed over the surface of the airfoil.
The blade structure illustrated in FIGS. 1, 2, and 3 includes a
hollow strut 23, which may be a cast structure, and which may be
cast integral with the blade base 8 or be otherwise secured to it.
Strut 23 may be the means to fix the blade wall to the blade base,
or part of such means. Strut 23 is of such contour as generally to
parallel the interior of the blade wall but be spaced a substantial
distance from it. It includes a number of cross walls 24 in the
preferred structure, these defining with the outer wall of the
strut a number of spanwise extending cooling air passages 26. A
layer of honeycomb material 27 defined by walls extending across
the gap from the strut 23 to the interior of the airfoil wall 7 is
bonded both to the wall and to the strut by any suitable process,
preferably diffusion bonding, although some such process as brazing
might be employed.
As shown more clearly in FIG. 4, the honeycomb material defines a
number of polyhedral cells 28, preferably hexagonal, terminating at
the airfoil wall and at the strut. Numerous apertures 30 are
provided in the wall of strut 23 to distribute the cooling air from
the passages 26 into the cells of the honeycomb. The size and
spacing of these apertures should be such as to meter the cooling
fluid to the respective areas of the blade as needed for proper
cooling, providing sufficient differential pressure between the
interior and the exterior of the blade for this purpose. The
apertures 30 may communicate with various ones of the cells 28 but
need not connect directly to all of the cells, since they are
interconnected as seems desirable through pores 31 in the walls of
the honeycomb. Thus air may flow through apertures 30 and pores 31
to the interior of wall 7. The nature of this distribution of air
is indicated by the flow arrows on FIGS. 3 and 4. In FIG. 3, the
airfoil or wall 7 is indicated as a porous structure by numerous
pores 32 through the wall. These are, in a sense, schematic since
the wall 7 may not have pores specifically as illustrated in the
FIG. 3. In many cases it is desirable to obtain a preferred wall
thickness by laminating layers of metal. However, for the present
purpose, the wall 7 as illustrated may be considered as a
representation of a porous wall of whatever structure is suitable
for the purpose. Several types of porous sheet material are
presently available commercially.
Because of the narrowness of the trailing edge portion of the
blade, the strut terminates considerably ahead of the trailing edge
but the strut may be provided with air discharge apertures 34 at
the trailing edge communicating with the honeycomb adjacent the
trailing edge which may have openings through the honeycomb wall,
generally as illustrated in FIG. 4, to conduct the fluid toward the
trailing edge of the blade. AS will be seen, with the blade wall
rigidly fixed to the struts through the honeycomb material, the
overall blade is extremely stiff and resistant to ballooning or
tinpanning, as well as rigid to resist bending because of the beam
loads due to the pressure of motive fluid on the blade. Also, the
honeycomb material provides a very suitable path for conduction of
cooling air from the strut to the porous surface of the blade with
a minimum of obstruction of the interior of the blade wall. Only
the narrow edges of the metal strips which define the honeycomb are
in abutting relation to the wall.
FIG. 5 illustrates a different structure, which is in some respects
simpler, and in which the strut such as 23 of FIG. 2 is omitted. In
the structure of FIG. 5, the blade base and airfoil may be as
previously described and are given the same reference numerals. In
this case, however, the blade wall 7 is reinforced by honeycomb
material extending from face to face of the blade and bonded to the
interior of the wall at both faces of the blade by diffusion
bonding or otherwise. In this structure, a number of cells 37 are
defined by walls indicated at 38, these walls defining a honeycomb
structure generally as indicated in FIG. 4, although the cells may
be of larger cross section. A number of spanwise extending passages
40 are machined in the honeycomb material, cutting through the
walls of the cells to distribute fluid from the blade base
throughout the length of the airfoil. These passages communicate
directly with many of the cells 37, which in turn direct the fluid
to the interior of the wall 7 through which it flows for
transpiration cooling. Moreover, apertures 42, as indicated at
various points, may be provided through the walls of the cells to
distribute fluid into various cells which do not otherwise
communicate with the spanwise extending passages 40. Since each
spanwise extending passage distributes fluid to a particular
portion of the chordwise extent of the blade, the cooling fluid may
be metered either by the size of the passage, by the entrance to
the passage, or otherwise so that the quantity of fluid is
appropriate to the requirements of the particular chordwise portion
of the blade. In this case, however, the pressure will be the same
on both faces of the blade. This may be a disadvantage, as it will
require that the porosity of the low-pressure surface be less than
that of the high-pressure surface of the blade wall. On the other
hand, the structure of FIG. 5 is lighter and simpler than that of
FIG. 2, and may have ample strength for many applications.
It will be apparent to those skilled in the art that the structures
described provide for reinforcement of the blade as a beam and also
for reinforcement of the sheet metal faces of the blade and for
efficient metering and distribution of cooling air to the blade
wall.
The detailed description of preferred embodiments of the invention
for the purpose of explaining the principles thereof is not to be
considered as limiting or restricting the invention, as many
modifications may be made by the exercise of skill in the art.
* * * * *