U.S. patent number 3,891,348 [Application Number 05/246,778] was granted by the patent office on 1975-06-24 for turbine blade with increased film cooling.
This patent grant is currently assigned to General Electric Company. Invention is credited to Thomas A. Auxier.
United States Patent |
3,891,348 |
Auxier |
June 24, 1975 |
Turbine blade with increased film cooling
Abstract
An air-cooled turbine blade having a plurality of serially
spaced cavities therein is provided with cooling air inlets at its
base. One of the inlets directs a cooling flow into a cavity
proximate the trailing edge of the blade for cooling the blade
surfaces defining this cavity. From this cavity, the flow is
directed in serpentine fashion into a second cavity remote from the
trailing edge for cooling the surfaces defining this latter cavity.
The cooling flow is then directed in a film from the second cavity
onto the outer surface of the blade for cooling the latter.
Inventors: |
Auxier; Thomas A. (Cincinnati,
OH) |
Assignee: |
General Electric Company
(Cincinnati, OH)
|
Family
ID: |
22932164 |
Appl.
No.: |
05/246,778 |
Filed: |
April 24, 1972 |
Current U.S.
Class: |
416/97R;
416/96A |
Current CPC
Class: |
F01D
5/189 (20130101); Y02T 50/60 (20130101) |
Current International
Class: |
F01D
5/18 (20060101); B63h 001/14 () |
Field of
Search: |
;416/90,97,233,95,231 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Feinberg; Samuel
Attorney, Agent or Firm: Bigelow; Dana F. Lawrence; Derek
P.
Government Interests
The invention herein described was made in the course of or under a
contract, or a subcontract thereunder, with the United States
Department of the Air Force.
Claims
What is claimed as new and desired to be secured by Letters Patent
of the United States is:
1. In a turbomachine, an air-cooled blade comprising:
a blade shell having an outer surface, first, second and third
inner surfaces, and a leading edge and a trailing edge;
a first cavity in said shell proximate said trailing edge and
formed by said first inner surface of said shell;
a second cavity in said shell remote from said trailing edge and
formed by said second inner surface of said shell;
a third cavity in said shell proximate said leading edge and formed
by said third inner surface of said shell;
means for introducing cooling air into said first cavity for
cooling said first inner surface;
means for introducing cooling air into said third cavity for
cooling said third inner surface;
a plurality of passageways formed through said trailing edge and
communicating with said first cavity for efflux of a first portion
of said first cavity cooling air therefrom;
means for directing the remainder of said first cavity cooling air
from said first cavity into said second cavity for cooling said
second inner surface; and
means for directing all of said cooling air delivered to said
second cavity in a film from said second cavity onto said outer
surface for cooling said outer surface.
2. The blade of claim 1 further comprising first and second blade
ends and a pair of ribs located internally of said shell and
extending between said first and second blade ends, wherein said
means for introducing cooling air into said first cavity is
disposed proximate said first blade end, and said means for
directing said cooling air into said second cavity comprises an
opening in one of said ribs disposed proximate said second blade
end.
3. The blade of claim 1 further comprising a radially outward tip
end and a radially inward platform wherein said means for directing
said cooling air onto said outer surface comprises a plurality of
spaced apertures providing communication between said second cavity
and said outer surface, disposed between said tip end and said
platform and substantially aligned along a radial line along said
blade shell.
4. The blade of claim 3 further including a hollow impingement
insert positioned within said second cavity, and said cooling air
directing means directs said remainder of said cooling air
initially to the interior of said insert.
5. The blade of claim 4 further including a second hollow
impingement insert positioned within said third cavity.
6. An air-cooled blade for use in a turbomachine, said blade
comprising:
a blade shell in the shape of an airfoil having a leading edge and
a trailing edge and further having an outer surface and first,
second and third inner surfaces and first and second ends;
a blade platform proximate the first end of said shell;
first, second and third serially spaced cavities defined
respectively by said first, second and third inner surfaces of said
shell and disposed respectively proximate said trailing edge,
remote from said trailing edge, and proximate said leading
edge;
a blade closure proximate the second end of said shell for
separating said cavities from an environmental atmosphere;
means for introducing a first flow of cooling air through said
platform into said first cavity for cooling said first inner
surface;
a plurality of passageways formed through said trailing edge and
communicating with said first cavity for efflux of a first portion
of said first cavity cooling air therefrom,
means proximate said closure for directing the remainder of said
first flow from said first cavity into said second cavity for
cooling said second inner surface;
means for directing all of said first flow delivered to said second
cavity in a film from said second cavity onto said outer surface
for cooling said outer surface;
means for introducing a second flow of cooling air through said
platform into said third cavity for cooling said third inner
surface; and
means for directing said second flow in a film from said third
cavity onto said outer surface for further cooling said outer
surface.
7. The blade of claim 6 wherein said means for directing said first
flow onto said outer surface comprises a plurality of spaced
apertures substantially aligned along a radial line between said
first and second ends of said blade shell.
Description
BACKGROUND OF THE INVENTION
This invention relates to blades for use in turbomachinery and,
more particularly, to air-cooled blades of the aforesaid
variety.
In turbomachinery, a flow of pressurized working fluid is directed
onto a plurality of turbine blades mounted upon rotatable discs for
imparting momentum thereto, whereby the kinetic energy of the fluid
flow may be transformed into torque. In a number of applications of
turbomachine concepts, and particularly with respect to turbojet
engines, the working fluid flow is heated to extremely high
temperatures, and travels at extremely high velocities. As a
result, it has become requisite to discover ways in which to
maintain the performance and reliability of turbine blades
subjected to such a working environment.
Improvements in metal alloys provided early solutions to the
contemporaneous problems of mechanical strength and heat resistance
of turbine blades. However, increased demands for performance and
ever larger power outputs have mandated blade design variations in
addition to improvements in material compositions. Objectives of
the design variations have been to provide means for passing
cooling fluids to or through portions of the blades subjected to
particular heating while reinforcing the structure of turbine
blades in the areas of particular mechanical stress.
Members of one variety of blades resulting from the application of
these criteria have included a plurality of radially extending
cavities serially spaced between the leading and trailing edges of
the blades. The cavities perform the function of directing a flow
of cooling fluid through the interior of the turbine blades in
order to cool respective portions thereof. Cross ribs extending
between adjacent cavities serve to increase the strength of the
blades in the directions of stress to which the blades are
subjected. In blades of this variety, it has been the conventional
practice to provide cooling air inlets to the cavities which open
through the base or tip of each blade to passages in the disc upon
which the blades are mounted or to a plenum surrounding the disc.
The cooling flow is passed from these inlets through the cavities
and eventually is dumped out of the cavities through exits into the
environment thereof for expulsion with the working fluid.
In modern, high-powered turbomachinery, overall operating
efficiency suffers when turbine blades are cooled by the
inefficient application of large amounts of cooling air to the
individual blades, since the work required to provide cooling air
negates a similar amount of output available from the engine.
Consequently, blades using minimum quantities of cooling fluid are
desirable. Thus, it has become increasingly important to make full
cooling use of the cooling fluid passed through each blade.
Variation of the flow path of the cooling fluid through the blades
has been suggested, whereby an increased portion of the available
cooling power of the fluid is utilized. A common approach has been
to direct a given cooling flow in a serpentine path serially
through a number of adjacent cavities prior to the expulsion
thereof. It has been further suggested in the prior art to pass a
flow of cooling fluid in this serpentine fashion from the trailing
edge cavity to one or more serially adjacent cavities before
expelling the cooling fluid from apertures near the blade base, tip
end and/or trailing edge. While the serpentine path of the fluid
increases the utilization of available cooling power, the dumping
of the used fluid from the tip, base end or trailing edge of the
blade fails to comprehend further use to which the cooling fluid
might be put, namely utilization of the fluid's film cooling
potential. This potential has in the past been utilized with
respect to cooling flow introduced into leading edge cavities. But
the film cooling potential remaining in trailing edge cooling flow
upon completion of its serpentine flow path has not been
appreciated.
SUMMARY OF THE INVENTION
It is therefore an object of the present invention to provide an
air-cooled turbine blade having a plurality of internal cavities
therein with means for further utilizing the cooling potential of a
flow of cooling air subsequent to the utilization of this air for
the cooling of the blade surfaces defining the internal
cavities.
It is a further object of the present invention to accomplish this
increased use of cooling potential by directing the flow of cooling
air from an internal cavity onto the outer blade surface in a
cooling film.
It is a more particular object of the present invention to perform
the directing of the cooling air as a film onto the outer blade
surface after completion by the air of a serpentine flow path
through serially adjacent internal cavities originating with the
trailing edge cavity.
The present invention seeks to more fully utilize the cooling power
of the quantity of cooling fluid supplied to turbine blade trailing
edge cavities by expelling particular portions of that fluid (which
otherwise would be dumped into the gas stream) in a film onto the
outer surface of the blade. In order to accomplish this, the
present invention provides a number of exit apertures communicating
the outer blade surface to the interior of a particular blade
cavity. This cavity is the one which the cooling flow reaches upon
completion of a predetermined flow path through the blade. The
apertures are arranged in a manner appropriate to the formation of
a cooling film upon the blade's outer surface. The resulting fluid
film serves to convectively remove heat from this surface as well
as to form a barrier against direct impingement upon the blade by
the hot working fluid. As a result, the external blade surface
temperature remains lower, so that less cooling air need be
provided. Consequently, the overall efficiency of the engine is
enhanced.
Further objects of the present invention will become apparent from
the detailed description of a preferred embodiment contained
hereinafter as illustrated by the following figures wherein:
FIG. 1 is a section view of a typical turbojet engine showing the
essential elements thereof;
FIG. 2 is a partial section view of the turbojet engine of FIG. 1
showing the turbine arrangement in greater detail;
FIG. 3 is a section view of the blade of FIG. 2 taken along lines
3--3;
FIG. 4 is a half-section view of the turbine blade of the present
invention; and
FIG. 5 is a schematic diagram of the flowpath of cooling air within
the turbine blade of FIG. 2.
DESCRIPTION OF A PREFERRED EMBODIMENT
The following description amplifies the particular embodiment of
the present invention depicted in the accompanying drawings. One
skilled in the art might easily recognize numerous changes which
may be made in the structure of this embodiment without departing
from the spirit of the present invention.
The turbojet engine depicted in FIG. 1 comprises the basic elements
of typical machinery of this variety. A substantially cylindrical
housing surrounds a compressor 10, combustors 11, and a turbine 12,
all disposed about rotatable shaft 13. As is well known in the art,
atmospheric air enters the machine from the left to be pressurized,
heated and expelled to the right to provide usable thrust. More
particularly, air enters from the left and is operated upon by the
compressor 10 (in combination with the shape of the lead end of
shaft 13) to be pressurized and directed, in part, into combustors
11. Heat energy is added to the air within the combustors by the
burning of appropriate fuel supplied thereto. Working fluid, which
is a combination of air and burned fuel, exits at the right end of
the combustors and impinges the plurality of turbine blades 14
carried by a number of adjacent discs making up the turbine 12. The
impingement of the turbine blades 14 by the working fluid serves to
drive the turbine in rotation, which rotation is imparted to shaft
13. The rotation of shaft 13 is the motivating force for the
operation of the compressor 10 at the forward end of the
machine.
Turbine blades 14 must be extremely strong and heat resistant in
order to withstand the force and heat of the impinging working
fluid. The cooling system of the present invention, by which the
blades 14 are protected from overheating, is depicted in FIGS. 2
through 5 and operates by making use of a portion of the air
operated upon by compressor 10 but not directed into the combustors
11.
FIG. 2 shows a typical turbine blade 14 and its cooperation with
shaft 13 and elements of the cooling system which are elucidated
hereinafter. Blade 14 includes a blade shell 16 in the shape of an
airfoil, and a platform 18 adapted to cooperate with disc 19 by
which the plurality of blades are supported. Blade shell 16 has an
outer surface 17 and a plurality of inner cavities which will also
be discussed hereinafter. At the blade tip (the blade end opposite
platform 18) is a closure 20 which separates the blade inner
cavities from environmental atmosphere, and which may be integral
with the blade shell 16 or a separate piece affixed thereto. The
blade shell 16 further has a leading edge 26 and a trailing edge
28.
In the embodiment of the invention disclosed in FIG. 2, an aperture
22 in shaft 13 permits the passage therethrough of cooling air from
a cooling air expander 24 cooperating with an appropriate plenum
(not shown) for the delivery of cooling air to the blade. It is
recognized that the present invention is equally applicable to
blades which are designed to be cooled by the application of air
provided through inlets located near the tip of the blade rather
than near the platform or by internal turbine circuits that do not
use a cooling air expander. The present embodiment is to serve only
as an example and not be considered the only embodiment of the
present invention.
The cross-sectional views of blade 14 depicted in FIGS. 3 and 4,
taken together with the schematic flow path of FIG. 5, disclose the
blade structure which directs the application of the cooling air
fed to the blade platform 18 as described above. FIGS. 3 and 4 show
that the turbine blade of the present embodiment of the invention
incorporates first, second and third cavities labeled 30, 32 and
34, respectively, which are disposed serially adjacent to one
another between leading edge 26 and trailing edge 28 of the blade
shell 16. The cavities are defined within the shell by inner shell
surfaces 31, 33 and 35, respectively. The three cavities are of
shape and size determined to be appropriate for the optimization of
cooling efficiency and mechanical blade strength. Cavity 30 is
disposed proximate trailing edge 28 of the blade, while cavity 32
is disposed remote from the trailing edge 28. Cavity 34 is disposed
proximate the leading edge of the blade.
Inserts 36 and 38 are disposed respectively within cavities 32 and
34, and respectively bear pluralities of orifices 37 and 39 for the
distribution of cooling air in an impinging flow against the inner
surfaces of each respective cavity. The inner surfaces 31 of cavity
30 are provided with a plurality of protrusions 31a appropriately
positioned to enhance the turbulence of flow for minimum pressure
drop. As defined by the state of the art, the impinging flow
associated with cavities 32 and 34 and the turbulent flow
associated with cavity 30 are superior in cooling characteristics
to the flows which would occur within the cavities absent the
provisions described.
The blade 14 of the present embodiment is provided with two inlets
40 and 42 for the entry of cooling fluid from passage 22 (see FIG.
2). It is noted that the two inlets 40 and 42 service cavities 30
and 34, respectively. Means for passing cooling fluid to cavity 32
includes a passage 44 between cavities 32 and 30 disposed in
proximity to the tip of blade 14 and remote from inlet 40. The two
cavities 30 and 32 and passage 44 define a serpentine path for the
cooling fluid entering inlet 40.
The definition of appropriate exits for the cooling fluid, which
exits combine with the foregoing blade structure to maximize the
utilization of the cooling fluid, accomplishes the objects of the
present invention. As in the prior art, a minor portion of the
cooling fluid which has been introduced through trailing edge inlet
40 is exhausted through a plurality of exit apertures 46 provided
at the trailing edge 28 of the blade shell 16. As is also prevalent
in the prior art, a portion of the air entering leading edge cavity
34 through inlet 42 is exhausted through three groups of exit
apertures 48, 50 and 52 positioned and adapted to direct the
exiting fluid in a film across various portions of the outer
surface of the blade shell 16.
Film cooling has been found to be useful to increase the use to
which cooling air may be put, whose cooling potential has not been
exhausted during application to the inner surfaces of the blade
shell. If, after passing from the inlet 42 and through orifices 39
in insert 38 and against surfaces 35, the air within cavity 34
remains at a temperature lower than that existing in the working
fluid near the outer surfaces of the blade shell 16, the passing of
this air out of cavity 34 in a film across such outer surfaces
would serve to cool them and thus to make further use of the
cooling flow. It is precisely to this film-cooling concept that the
present invention is directed.
While the prior art has comprehended the use of exit film cooling
to maximize the utilization of the cooling power of air fed into
leading edge cavities, it has been common practice with respect to
cooling flow fed into trailing edge cavities to dump the flow out
of exit apertures at the tip, base or trailing edge of the blade
after an internal serpentine path has been completed. Wherever the
working fluid near the outer surfaces of the blade to which this
latter flow might be directed is at a temperature higher than the
exiting cooling flow, this practice constitutes a waste of cooling
power.
The present invention thus provides a plurality of spaced exit
apertures 54 through which the cooling fluid may be directed onto
the outer surface of blade shell 16 downstream of apertures 54.
Apertures 54 are located substantially along a radial line between
the ends of blade shell 16 and are configured appropriately for the
formation of a cooling film upon the outer blade surface. The film
thus formed serves as a barrier to protect the blade from the
direct impingement of the hot working fluid. Further, the film
serves to remove heat from the blade surface by convective heat
flow. This added usage of the cooling power of the cooling fluid
allows the turbine blade to be cooled to the same extent as
previously, but with the expenditure of less cooling fluid. As
described above, beneficial effects upon the overall efficiency of
the turbomachine are thus achieved.
The operation of the cooling system of the present invention will
now be described with the aid of the alphabetical designations of
locations depicted in FIGS. 3 and 4 and represented schematically
in FIG. 5. Cooling air from the plenum is passed through air
passage 22 of FIG. 2 to the platform 18 of blade 14 and into inlets
40 and 42 of FIG. 4. That portion of the flow entering inlet 42
passes from point A below cavity 34 to point B within cavity 34 and
into contact with insert 38. The air is passed through orifices 39
and into the area represented by point C, which is defined by the
insert 38 and inner surfaces 35 of the blade shell. The impingement
of this air against surfaces 35 serves to cool these surfaces
before the air is exhausted through exit apertures 48 and 50 to
points D and E, respectively. The working fluid flowing past points
D and E impinges the exiting cooling fluid and, due to the viscous
forces therebetween, creates films to the downstream sides of each
point which films serve to cool the external surfaces of the blade
shell 16 until the films are separated therefrom by turbulence.
The second portion of cooling air flowing into the blade (through
inlet 40) passes from point F below the blade shell to point G
proximate the blade tip closure 20. Since the flow enters the blade
at the trailing edge at its coolest temperature, a minimum portion
of this fluid is forced out of cavity 30 through trailing edge exit
apertures 46. The predominant portion of the fluid passes through
passage 44 from point G to point H within cavity 32. This flow
continues past point I within cavity 32 and to point J. While
within cavity 30, the cooling fluid acts in turbulent flow to cool
surfaces 31. Having passed into cavity 32, the fluid is directed by
orifices 37 of insert 36 into the area represented by point K and
into impingement with surfaces 33 for the cooling thereof. Having
progressed to this point and having been raised in temperature by
contact with surfaces 31 and 33 of the blade shell, the cooling
fluid remains at a temperature below the external surface
temperature of the blade shell. Thus, the fluid still possesses
usable cooling power. Accordingly, there are provided apertures 54
through which the fluid is subsequently passed to point L outside
of the blade shell. The viscous forces of the passing working fluid
act upon the exiting cooling fluid to create a cooling film
downstream of exit orifices 54 upon the outer surface of the blade
shell proximate trailing edge 28. This film forms a barrier between
the outer blade surface and the working fluid. The film also cools
the blade surface by convective heat transfer. Consequently, the
film serves to further cool the blade by increasing heat transfer
to the cooling fluid after its exit from the blade.
In this way, the present invention increases the utilization of the
cooling power of a given quantity of cooling fluid by maximizing
the contact with various turbine blade shell surfaces of that
portion of the cooling fluid fed into trailing edge cavities. Were
the fluid entering inlet 40 to be dumped into the passing working
fluid from either the tip or base ends of the blade shell, no film
would be created upon the outer surface of the blade by this fluid,
and the remaining cooling power thereof would be wasted. By the
application of the present invention to turbine blades, reductions
in the amount of cooling fluid required to be fed to the rear or
trailing edge blade cavities may be effected, with attendant
increases in machine efficiency.
While the present invention has been described in conjunction with
a preferred embodiment thereof, it is apparent that numerous
variations in the application thereof may be made without departing
from the spirit of the invention. For example, a turbine blade
having a plurality of cavities in a number of larger than the three
disclosed might be devised wherein cooling air fed to one of the
cavities proximate the trailing edge is passed in a serpentine path
through serially adjacent cavities and finally exhausted in a
cooling film upon external blade surfaces. Another variation, which
was discussed briefly above, might involve the application of
cooling fluid through inlets located near the tip rather than the
platform of the blade shell. Additionally, while the embodiment
herein disclosed passes a cooling film over only one side of the
outer surface of the blade shell, a plurality of apertures could
easily be applied which would serve to communicate the other side
of the shell to a trailing edge cavity for the passing of cooling
fluid thereacross.
Other modifications of the described embodiment of the invention
will occur to those skilled in the art within the scope of the
present inventive concept without departing from the spirit
thereof.
* * * * *