U.S. patent number 3,806,276 [Application Number 05/284,716] was granted by the patent office on 1974-04-23 for cooled turbine blade.
This patent grant is currently assigned to General Motors Corporation. Invention is credited to Robert H. Aspinwall.
United States Patent |
3,806,276 |
Aspinwall |
April 23, 1974 |
COOLED TURBINE BLADE
Abstract
A turbine blade is cooled internally by air discharged through
perforations in a liner toward the interior of the blade wall. The
liner is spaced from the blade wall by ribs on the wall extending
spanwise of the blade. The ribs increase in height toward the blade
tip so that spanwise-extending diverging passages for discharge of
the cooling gas at the tip of the blade are provided. The liner is
of a relatively high conductivity material such as a cuprous nickel
alloy. The exterior of the liner is artificially roughened to
increase the absorptivity of the liner to radiated heat. The blade
has a base into which the liner extends so as to conduct some of
the heat through the liner into the base, which is relatively
isolated from the hot motive fluid to which the blade is
subjected.
Inventors: |
Aspinwall; Robert H.
(Zionsville, IN) |
Assignee: |
General Motors Corporation
(Detroit, MI)
|
Family
ID: |
23091254 |
Appl.
No.: |
05/284,716 |
Filed: |
August 30, 1972 |
Current U.S.
Class: |
416/97R; 415/115;
416/96A; 416/193A |
Current CPC
Class: |
F01D
5/189 (20130101); F05D 2260/201 (20130101) |
Current International
Class: |
F01D
5/18 (20060101); F01d 005/18 () |
Field of
Search: |
;416/96,97,92,95
;415/115,116 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Powell, Jr.; Everette A.
Attorney, Agent or Firm: Fitzpatrick; Paul
Claims
I claim:
1. An internally-cooled flow-directing member for a turbomachine
comprising, in combination, a hollow airfoil having an external
wall defining an internal chamber, a liner disposed in the airfoil
and spaced from the wall, the member having an inlet for a cooling
gas at one end of the airfoil and an outlet for the cooling gas at
the other end of the airfoil, the wall bearing internal ribs
extending spanwise of the airfoil and engaging the liner, the ribs
increasing in height toward the cooling gas outlet so that cooling
gas passages diverging toward the airfoil outlet are defined by the
wall and liner between the ribs, the inner surface of the wall
having a relatively smooth finish for high heat emissivity and the
outer surface of the liner having a relatively rough finish for
high heat absorptivity, and the liner being made of a material of
relatively high coefficient of thermal conductivity as compared to
the airfoil.
2. An internally-cooled flow-directing member for a turbomachine
comprising, in combination, a hollow airfoil having an external
wall defining an internal chamber, a liner disposed in the airfoil
and spaced from the wall, the liner having an inlet for a cooling
gas and defining distributed perforations for discharge of the gas
toward the wall, the airfoil defining an outlet for the cooling
gas, the wall bearing internal ribs extending spanwise of the
airfoil and bonded to the liner, the inner surface of the wall
having a relatively smooth finish for high heat emissivity and the
outer surface of the liner having a relatively rough finish for
high heat absorptivity, the liner being made of a material of
relatively high coefficient of thermal conductivity as compared to
the airfoil.
3. An internally-cooled flow-directing member for a turbomachine
comprising, in combination, a hollow airfoil having an external
wall defining an internal chamber, a liner disposed in the airfoil
and spaced from the wall, the liner having an inlet for a cooling
gas and defining distributed perforations for discharge of the gas
toward the wall, the airfoil defining an outlet for the cooling
gas, the inner surface of the wall having a relatively smooth
finish for high heat emissivity and the outer surface of the liner
having a relatively rough finish for high heat absorptivity, the
liner being made of a material of relatively high coefficient of
thermal conductivity as compared to the airfoil; the airfoil having
a base isolated from the flow passing by the airfoil and including
an inlet for the cooling gas, the liner extending into the
base.
4. An internally-cooled flow-directing member for a turbomachine
comprising, in combination, a hollow airfoil having an external
wall defining an internal chamber, a liner disposed in the airfoil
and spaced from the wall, the liner having an inlet for a cooling
gas and defining distributed perforations for discharge of the gas
toward the wall, the airfoil defining an outlet for the cooling gas
at the tip of the airfoil, the wall bearing internal ribs extending
spanwise of the airfoil and engaging the liner, the ribs increasing
in height toward the airfoil tip so that cooling gas passages
diverging toward the airfoil tip are defined by the wall and liner
between the ribs, the inner surface of the wall having a relatively
smooth finish for high heat emissivity and the outer surface of the
liner having a relatively rough finish for high heat absorptivity,
the liner being made of a material of relatively high coefficient
of thermal conductivity as compared to the airfoil; the airfoil
having a base isolated from the flow passing the airfoil and
including an inlet for the cooling gas, the liner extending into
the base.
Description
My invention is directed toward improvements in the structure of
cooled flow-directing members for turbomachines working with hot
motive fluids. Such fluid-directing members commonly are the rotor
blades and nozzle vanes of turbines such as gas turbines.
Hereinafter they will be referred to as blades for conciseness.
Regardless of the advances in metallurgy which have provided
increasingly high temperature resistance in alloys used for turbine
blades, there remains a need for improved means for cooling such
blades, to increase the maximum temperature level of the engine in
which they are employed. The reason for high temperature levels is
greater efficiency and a lighter weight and more compact power
plant.
It is important that cooling be as effective as possible so as to
minimize loss of power or efficiency due to the provision of
cooling air or other medium for cooling the blades.
My invention is directed to improved structure for internally
cooling a turbine blade or vane of a non-porous wall type. The
preferred structure of my invention involves a liner from which
cooling air is spouted through small perforations toward the wall
of the blade, the liner being spaced from the blade wall by ribs
extending inward from the wall. Such structures are known.
According to my invention, however, the liner is made of a material
of relatively high conductivity such as cuprous nickel material and
thus has greater than usual ability to conduct some heat out of the
airfoil into the blade base. Also, transfer of heat by radiation
from the blade wall to the liner is improved by providing a rough
surface on the liner to increase the thermal absorptivity of the
liner.
The principal objects of my invention are to provide improved means
for cooling flow-directing members for high temperature machines,
to provide a cooled blade which is of simple and readily fabricated
structure, and to provide a system having maximum effectiveness for
cooling a blade by internal convection and radiation, as
distinguished from transpiration cooling.
The nature of my invention and its advantages will be clear 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 much enlarged transverse section of the blade taken on
the plane indicated by the line 2--2 in FIG. 1.
FIG. 3 is a somewhat enlarged longitudinal section of the blade
taken in the plane indicated by the line 3--3 in FIG. 2.
FIG. 4 is a greatly enlarged fragmentary view of a portion of the
blade wall and liner taken in a plane extending spanwise of the
blade.
FIG. 5 is a fragmentary cross section taken on the plane indicated
by the line 5--5 in FIG. 4.
FIG. 6 is a fragmentary view illustrating a modified blade
structure.
Referring first to FIGS. 1 and 2, FIG. 1 illustrates a blade, the
general outline of which may be conventional. The flow-directing
member or blade 2 comprises an airfoil or blade portion 3, a
platform 4, and a base 6. The platforms of adjacent blades define
one boundary of the hot motive fluid path through a cascade of
blades. The platform isolates the base 6 from direct contact with
the motive fluid. The base 6 comprises a hollow stalk 7 and a
dovetail or serrated root 8 adapted for mounting in a turbine rotor
structure. Referring particularly to FIG. 2, the hollow blade 3 is
defined by a wall 9 and is illustrated as having a suitable
cambered airfoil configuration, having a leading edge 10, a
trailing edge 11, a convex face 12, and a concave face 14. The
blade wall defines an internal chamber 15 of generally airfoil
shape, and the tip of the blade at 16 is open. The blade stalk 7
defines an entrance 18 for cooling gas, ordinarily compressor
discharge air in a gas turbine engine. A hollow sheet metal liner
19, the surface of which may be considered to be parallel in a
rough way to the wall 9, is disposed within the chamber 15.
As illustrated in FIG. 3, the upper end of the liner is closed by a
junction between the two side walls of the liner at 20. The base
end of the liner may be disposed in slots 22 in the wall of the
stalk and suitably fixed there. This is beneficial to conduction of
heat from the liner into the blade stalk. Since the stalk first
receives the cooling gas and is not in direct contact with the hot
motive fluid, it is normally much cooler than the blade wall 9.
The interior of the blade wall 9 bears generally parallel ribs 23
which extend into contact with the blade liner and which, as will
be apparent from FIG. 3, increase in height toward the tip of the
blade. As a result, spanwise-extending passages 24 defined between
the blade wall 9 and the liner 19 and bounded by the ribs 23
increase in depth and area towards the tip of the blade to maintain
a more or less constant velocity of flow along the passages as the
volume of flow increases. Cooling air which enters the opening 18
in the open blade base end of the liner is discharged through a
multiplicity of small perforations or spouting holes 26 distributed
along each passage 24. The liner 19 is bonded to the ribs 23 by
brazing, diffusion bonding, or other suitable process, as indicated
at the points 27 in FIG. 5. In addition to the outlet at the tip of
the blade, the trailing edge of the blade may be formed with slots
28 to discharge some cooling air at this point to improve the
cooling at the narrow trailing edge.
The airfoil tube apart from the liner may be formed by casting or
forging and normally will be of a high nickel alloy such as
ordinarily are used in hot situations and may be what are commonly
called superalloys. These alloys have relatively low thermal
conductivity. The liner 19, on the other hand, is preferably made
of a cuprous nickel alloy having relatively high thermal
conductivity.
The interior of the blade wall and the ribs 23 ordinarily are left
with a relatively smooth finish such as results from the
manufacture. The liner, on the other hand, is artificially
roughened to provide higher heat absorptivity as shown more clearly
in FIGS. 4 and 6. Preferably, this roughening is in the form of
contiguous parallel V-grooves 30 preferably of about 90.degree.
included angles. This roughness may be produced by etching or by
machining or by a process of rolling the sheet as desired. The
relatively smooth surface of the blade wall gives it a gray body
characteristic, whereas the rough surface of the liner gives it
more of a black body characteristic. The relatively higher
absorptivity of the liner and the relatively higher emissivity of
the wall improve the transmission of heat by radiation from the
wall to the liner. This is not the major means for removal of heat
from the wall 9, the principal removal being by transfer of heat to
the cooling gas. Nevertheless, any improvement in cooling is
important.
Thus, we have a very hot wall, the outer surface of which may be
1,000.degree. F. hotter than the cooling air in the interior of the
liner. The inner surface of the blade wall is substantially cooler
than its outer surface, the ribs cooler yet, and the liner 19 still
cooler. Because of the high heat transmitting characteristics of
the liner, it is more effective in transmitting heat from the ribs
to the cooling air, providing additional effective surface for
convection cooling. In the bonded joint there is good transfer of
heat from the ribs to the liner. Since the liner is a good heat
conductor, it also is instrumental in conducting heat toward the
base of the blade into the area which is remote from the motive
fluid stream above the platform 4. Also, because of the greater
absorptivity of the ridged or roughened surface of the liner, the
transfer of heat from the wall by radiation to the liner is
improved. The liner, of course, is cooled by the cooling air
flowing within the liner and through the holes 26 through the liner
as well as by the air flowing through the passages 24 which air, of
course, receives most of its heat from the wall 9.
It may be helpful to give an example of preferred dimensional
values in a blade as described above. The blade may be considered
to have a chord of about 1 1/2 inches, with a rib every 50 mils (a
mil being a thousandth of an inch), the ribs being 10 mils wide,
and the air holes 26 about 6 mils in diameter. The distance from
the liner to the blade wall increases from about 12 mils to about
40 mils from base to tip of the blade, the blade wall is about 40
mils thick, and the liner is about 10 mils thick. The ridges or
grooves 30 on the liner are about 3 mils deep. Such dimensions are
subject to change, of course, depending upon the nature of the
particular installation and exercise of engineering analysis.
The blade 2 may be cast integrally in one piece, following, for
example, the techniques described in McCormick U.S. Pat. No.
3,192,578, July 6, 1965, or the airfoil and base may be cast
separately and joined by a welding or diffusion bonding operation.
Or, if desired, the structure may be cast in two parts which are
then bonded together as illustrated generally in FIG. 6. The blade
34 of FIG. 6 is made of two parts 35 and 36, each defining one side
of the blade or airfoil 38, of the platform 39, of the stalk 40,
and of the root 42. These are united along a joining surface 43
which ordinarily, in practice, might approximately follow the mean
camber line of the blade. The ribbed interior of the blade and
other details are not indicated in FIG. 6.
It should be apparent to those skilled in the art that I have
conceived a significant improvement in the principles of internal
cooling of blades, giving greater efficiency in the use of cooling
air and greater uniformity of temperature throughout the blade.
The 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, since many
modifications may be made by the exercise of skill in the art.
* * * * *