U.S. patent number 3,806,275 [Application Number 05/284,715] was granted by the patent office on 1974-04-23 for cooled airfoil.
This patent grant is currently assigned to General Motors Corporation. Invention is credited to Robert H. Aspinwall.
United States Patent |
3,806,275 |
Aspinwall |
April 23, 1974 |
COOLED AIRFOIL
Abstract
A hollow air-cooled turbine blade has a web extending from face
to face of the blade to divide the interior of the blade into two
spanwise-extending chambers. A thin sheet metal liner is disposed
in each chamber, the liner having perforations distributed over its
surface and having projections to space it from the blade wall. The
liner is flexible and may be folded substantially flat for
insertion into the end of the blade. At the leading edge of the
blade, the liner walls are recurved to define a generally
parallel-walled slot nozzle extending spanwise of the blade.
Additional holes are placed along the outlet from this nozzle to
flow additional air for entrainment by the jet emerging from the
slot nozzle to improve cooling of the leading edge. Cooled air
enters the liners through the blade stalk and is discharged
preferably through the tip and trailing edge of the blade.
Inventors: |
Aspinwall; Robert H.
(Zionsville, IN) |
Assignee: |
General Motors Corporation
(Detroit, MI)
|
Family
ID: |
23091250 |
Appl.
No.: |
05/284,715 |
Filed: |
August 30, 1972 |
Current U.S.
Class: |
416/97R;
416/193A; 415/115 |
Current CPC
Class: |
F01D
5/189 (20130101) |
Current International
Class: |
F01D
5/18 (20060101); F01d 005/18 () |
Field of
Search: |
;416/92,96,97,95
;415/115 |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
|
|
|
|
|
|
|
491,903 |
|
Apr 1953 |
|
CA |
|
1,222,565 |
|
Feb 1971 |
|
GB |
|
Primary Examiner: Powell, Jr.; Everette A.
Attorney, Agent or Firm: Fitzpatrick; Paul
Claims
I claim:
1. An internally cooled turbine blading element comprising, in
combination, a hollow blade having leading and trailing edges and
defining a spanwise-extending chamber, and a perforated blade liner
disposed in the chamber, the end of the blade defining an opening
for insertion of the liner, the liner conforming generally to the
contour of the interior of the blade and being spaced from the
blade wall, the liner including means defining a spanwise-extending
slot nozzle for discharge of a cooling fluid directed at the
leading edge of the blade and generally cylindrical diverging walls
at the outlet of the nozzle, and defining perforations through the
said diverging walls for flow of additional cooling fluid for
entrainment by the flow through the slot nozzle.
2. An internally cooled turbine blading element comprising, in
combination, a hollow blade having leading and trailing edges and a
web disposed intermediate the said edges, so that the blade defines
two spanwise-extending chambers, one at each side of the web, and a
perforated blade liner disposed in each chamber, the end of the
blade defining openings for insertion of the liners, each liner
conforming generally to the contour of the interior of the blade
and being spaced from the blade wall, the liner at the leading edge
of the blade including means defining a spanwise-extending slot
nozzle for discharge of a cooling fluid directed at the leading
edge of the blade and generally cylindrical diverging walls at the
outlet of the nozzle, and defining perforations through the said
diverging walls for flow of additional cooling fluid for
entrainment by the flow through the slot nozzle.
3. An internally cooled fluid-reacting member for a turbomachine
comprising, in combination, wall means defining a blade with a
central chamber having an opening at one end of the blade, a
tubular perforated liner of thin flexible sheet metal disposed in
the chamber, and spacer means maintaining a separation between the
liner and the wall means over the major portion of the area of the
liner, the liner being collapsible for insertion into the chamber
through the said opening and being expandable by air pressure after
such insertion to the extent allowed by the spacer means, the liner
including means at the leading edge of the blade defining a
spanwise-extending slot nozzle for a discharge of a cooling fluid
directed at the leading edge of the blade and generally cylindrical
diverging walls at the outlet of the nozzle, and defining
perforations through the said diverging walls for flow of
additional cooling fluid for entrainment by the flow through the
slot nozzle.
4. An internally cooled turbine blading element comprising, in
combination, a root, a stalk, and a hollow blade extending from the
stalk, the blade having leading and trailing edges and defining a
spanwise-extending chamber, and a perforated blade liner disposed
in the chamber, the stalk and the stalk end of the blade defining
openings for insertion of the liner, the liner conforming generally
to the contour of the interior of the blade and being spaced from
the blade wall, the liner including means defining a
spanwise-extending slot nozzle for discharge of a cooling fluid
directed at the leading edge of the blade and generally cylindrical
diverging walls at the outlet of the nozzle, and defining
perforations through the said diverging walls for flow of
additional cooling fluid for entrainment by the flow through the
slot nozzle.
5. An internally cooled turbine blading element comprising, in
combination, a root, a stalk, and a hollow blade extending from the
stalk, the blade having leading and trailing edges and a web
disposed intermediate the said edges, so that the blade defines two
spanwise-extending chambers, one at each side of the web, and a
perforated blade liner disposed in each chamber, the stalk and the
stalk end of the blade defining openings for insertion of the
liners, each liner conforming generally to the contour of the
interior of the blade and being spaced from the blade wall, the
liner at the leading edge of the blade including means defining a
spanwise-extending slot nozzle for discharge of a cooling fluid
directed at the leading edge of the blade and generally cylindrical
diverging walls at the outlet of the nozzle, and defining
perforations through the said diverging walls for flow of
additional cooling fluid for entrainment by the flow through the
slot nozzle.
Description
DESCRIPTION
My invention is directed to improved cooled turbine blades and the
like. My invention is particularly directed to improved structures
employing the principles of convection and impingement cooling. As
used here, the term convection cooling refers to the transfer of
heat from the interior of a blade wall to a cooling medium flowing
along the wall. Impingement cooling is a variation of convection
cooling in which the cooling medium is directed as a sheet or jet
toward the wall to be cooled, thereby improving the efficiency of
the heat transfer or providing for increased heat transfer in
particular localities such, for example, as the leading edge of a
blade. The invention is particularly concerned with improvements of
the cooling of the blade leading edge and with improved structure
of a blade liner for this purpose. It is also concerned with a
blade liner which may readily be installed in a previously
completed turbine blade such as a cast blade, for instance.
Convection cooling of a blade wall, as distinguished from
impingement cooling, is described in Zimmerman U.S. Pat. No.
2,859,011, Nov. 4, 1958, and Emmerson et al, U.S. Pat. No.
3,446,480, May 27, 1969. Impingement cooling by air spouting from
blade liners against the wall of a blade is described in Weise et
al, U.S. Pat. No. 2,873,944, Feb. 17, 1959. A blade including a
liner with special provisions for jetting air to the leading edge
of the blade for impingement cooling is disclosed in Giesman et al,
U.S. Pat. No. 3,635,587, Jan. 18, 1972.
The general object of my invention is to provide improved structure
to accomplish the sort of cooling described in these prior art
patents and to provide a structure particularly suited to
fabrication.
The nature of my invention and its advantages will be apparent to
those skilled in the art from the succeeding detailed description
and accompanying drawings of the preferred embodiment of the
invention.
FIG. 1 is a fragmentary sectional view of a turbine wheel with a
blade mounted thereon.
FIG. 2 is an axonometric view of a turbine blade.
FIG. 3 is a transverse sectional view of the blade taken on the
plane indicated by the line 3--3 in FIG. 1.
FIG. 4 is a greatly enlarged view of the leading edge portion of
FIG. 3.
FIG. 5 is a fragmentary axonometric view of the blade liner.
FIG. 6 is a graph illustrating certain parameters of impingement
cooling.
Referring first to FIGS. 1 and 2, there is illustrated a turbine
wheel 2 having a rim 3 on which are mounted a ring of
fluid-reacting members or blading members 4, commonly known as
blades. Each blade comprises a dovetail root 6, a stalk 7, a
platform 8, and a blade proper or airfoil 10. The airfoil, as shown
most clearly in FIG. 3, is hollow and has a leading edge at 11, a
trailing edge at 12, a convex face 14, and a concave face 15, these
faces extending from one edge to the other. A web 16 adjacent the
maximum thickness zone of the blade joins the two faces or walls to
define with the blade wall a chamber 18 extending from the leading
edge to the web 16 and a chamber 19 extending from the web 16 to
the trailing edge. These chambers extend spanwise of the blade
through the platform and to the tip of the blade which is partially
closed by a tip closure 20.
The stalk 7 is made up of two webs 22 diverging from the root to
the platform which define between them an air space 23 having
openings at the forward and rear faces of the stalk. The space
within the stalk communicates through the open inner end 24 of the
blade with the chambers 18 and 19.
The blade root 6 is mounted in a suitably serrated slot in the
wheel rim 3. The blade is retained and flow of fluid between the
wheel rim and platforms is prevented by two cover plates or rings
of cover plates 26 and 27. These cover plates may be unitary or
segmented. The details are immaterial to the invention. Such plates
are shown in U.S. Pat. No. 3,446,480 referred to above, and in
White U.S. Pat. No. 3,034,298, May 15, 1962, for example. Holes 28
in the plate 26 and 30 in the plate 27 provide for entry of cooling
air or other medium from a suitable source (not illustrated) into
the space between the cover plates and the blade stalk, from which
the fluid flows into the blade stalk and thus into the passages 18
and 19. The fluid ultimately exhausts through openings 31 and 32 in
the blade tip closure forward and rearward of the web 16,
respectively. Also, preferably, the trailing edge of the blade is
formed with outlets such as slots 34 for exhaust of cooling air at
this point.
The structure as so far described may be considered part of the
known state of the art. To indicate generally the scale of the
drawings, the specific blade shown has a chord of about two
inches.
To provide for air impingement and better flow of the cooling air
along the interior of the surface of the blade wall, blade liners
35 and 36 are provided extending spanwise of the blade in chambers
18 and 19, respectively. These liners are open at the platform end
of the blade and closed at the tip of the blade, and are made of
very thin flexible heat resisting sheet metal, preferably about
three to five thousandths inch thick. The liners are preferably
spaced about twenty-five thousandths inch from the blade wall, the
spacing being accomplished by embossed projections 38 extending
outwardly from the liner. The liners have folds as indicated at 39
in the liner 35 and correspondingly in the liner 36. With these
folds, the liner may be flattened or collapsed as indicated
generally by the broken line 40 so that the flattened liner may be
inserted into the air space 23 in the blade stalk and pushed on
into the chamber 18 or 19. The liners may be made of such thin
flexible material because they are not a structural element of the
blade and are contained or supported by the walls of the blade and
the internal air pressure. After insertion, the liner may be
expanded into contact with the blade wall by forcing a blast of
fluid into the liner. Each liner has numerous small perforations
distributed over its surface as indicated generally at 41 in FIGS.
2, 4, and 5. Air which flows from the liner through these holes
impinges against the inner surface of the blade wall and flows
between the blade wall and liner to the outlets at 31, 32, and 34.
These perforations may be about seven thousandths inch in
diameter.
Considering now the structure of the liner 35 at the leading edge
of the blade (FIGS. 4 and 5), the two sides or faces of the liner
are recurved to define the side walls 42 of a slot nozzle 43. As
shown most clearly in FIG. 5, these side walls are united by
spacers 44 which are strips extending between the two walls 42 and
brazed, welded, or otherwise fixed to them. The slot nozzle at its
discharge end thus terminates in generally cylindrical outwardly
flaring wall sections 46. A row of holes 47 extends through each of
these wall sections 46 in position to deliver cooling air into the
sheet of air issuing from the slot nozzle 43.
The distance from slot 43 to the interior of the leading edge of
the blade may be about fifty thousandths of an inch and the width
of the slot preferably at least as great as one-eighth that
distance, preferably about seven thousandths. The jet issuing from
the slot nozzle has a greater penetrating power than that issuing
from a simple hole such as 41 through the sheet metal. However, the
distance from the holes 41 to the blade wall is less.
With the flat jet issuing from the nozzle 43, this moving sheet of
air tends to draw air from the holes 47 in the flaring part of the
slot nozzle, which air mixes with the flow from the slot nozzle and
creates a greater mass flow, greater momentum, and greater
turbulence at the point of impingement for greater removal of heat
from the blade leading edge.
FIG. 6 shows curves of heat transfer coefficient as a function of
the ratio of nozzle to plate spacing to nozzle width, the upper
curve indicating conditions with the turbulence promoter
(additional air through 47). It will be noted that the heat
transfer coefficient is significantly higher with the turbulence
promoter, particularly as nozzle to plate spacing decreases below
eight times the width of the nozzle.
The impingement tubes 35 and 36 may be fixed to the nozzle by
welding, diffusion bonding, or a brazing operation at the area of
the platform 8. Preferably, the margins of the liner are spread to
lie under the platform and are electron beam welded to the platform
at that point. Alternatively, the liners may be welded to the
interior of the blade at its base. While it is considered less
feasible, it should be noted that the spacing of the liner from the
blade may be accomplished by protrusions from the inside of the
blade rather than from the projections 38 on the liner.
As a matter of fabrication, it is also possible to diffusion bond
the liner to the interior of the blade or airfoil and thereafter
fix the blade to the base or other mounting structure. In the case
of a turbine nozzle, which may be regarded as a special case in
which the blades are stationary, the attachment of the blade to the
shrouds or other structure defining the flow path through the
turbine may follow known practice. In this case, since there is no
centrifugal force on the vane, retention of the liner is easier. If
the liner is open at both ends, and the vane is supplied with air
from both ends, there is not even any gas pressure tending to
displace the liner.
The detailed description of the preferred embodiment 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.
* * * * *