U.S. patent number 3,700,348 [Application Number 04/752,736] was granted by the patent office on 1972-10-24 for turbomachinery blade structure.
This patent grant is currently assigned to General Electric Company. Invention is credited to Charles E. Corrigan, Robert J. Corsmeier, Thomas G. Howell, Bernard L. Koff.
United States Patent |
3,700,348 |
Corsmeier , et al. |
October 24, 1972 |
TURBOMACHINERY BLADE STRUCTURE
Abstract
An economically fabricated turbomachinery blade structure with
good and predictable high temperature characteristics having a
hollow integrally cast member defining the blade portion, the
platform portion, a transition shank portion defining an opening to
the blade chamber and a pair of juxtaposed rails extending
therefrom. A hollow insert, formed with a plurality of nozzles in
the side walls thereof, is secured within the cast member chamber
so as to direct coolant fluid against the inner surfaces of the
blade portion. To provide means enabling attachment of the blade to
a supporting rotor, in one form, the juxtaposed rails are formed
into abutting contact at their free ends and bonded. In another
form, a root insert is provided which is secured to the inner
surfaces of shank rails. Suitable passages are provided to direct
coolant fluid into the insert chamber and to discharge the coolant
fluid through the trailing edge and the end closure of the blade.
Means may be provided to automatically space the insert nozzles
from the blade side walls. A plurality of posts may be provided in
the trailing edge portion of the blade to increase the effective
convection cooling area. All bonds subjected to structural loading
are spaced from the blade portion and positioned to be bathed in
coolant fluid so as to reduce their operating temperature
environment.
Inventors: |
Corsmeier; Robert J.
(Cincinnati, OH), Howell; Thomas G. (West Chester, OH),
Corrigan; Charles E. (Cincinnati, OH), Koff; Bernard L.
(Cincinnati, OH) |
Assignee: |
General Electric Company
(N/A)
|
Family
ID: |
25027599 |
Appl.
No.: |
04/752,736 |
Filed: |
August 13, 1968 |
Current U.S.
Class: |
416/90R; 416/95;
416/231R; 416/96A; 416/92; 416/96R; 416/97R |
Current CPC
Class: |
F01D
5/189 (20130101); F05D 2260/201 (20130101) |
Current International
Class: |
F01D
5/18 (20060101); B64c 011/24 () |
Field of
Search: |
;416/90,91,92,95,231,232
;29/156.8 |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
|
|
|
|
|
|
|
926,397 |
|
Apr 1955 |
|
DT |
|
685,769 |
|
Jan 1953 |
|
GB |
|
Primary Examiner: Feinberg; Samuel
Claims
What is claimed is:
1. A turbomachinery blade structure comprising:
a hollow, integrally cast member including a platform portion
adapted to define, in part, an inner boundary of a motive fluid
passage, a blade portion projecting from said platform portion, a
transition shank projecting from said platform portion generally
oppositely to said blade portion and defining an opening to said
hollow cast member, and a pair of juxtaposed shank rails projecting
from said transition shank;
a hollow insert slideably received within said hollow cast member
blade portion in spaced relationship thereto, said insert formed
with an open inner end for receiving a coolant fluid, a closed
outer end and a plurality of apertures for impinging said coolant
fluid against said cast member blade portion;
means for discharging said coolant fluid from said hollow cast
member blade portion;
a mounting collar formed with a passage therethrough, the open end
of said insert secured to said collar in flow communication with
said collar passage, said collar including a flange secured to said
tubular shank in closing relationship to said shank opening;
means enabling attachment of said blade structure to a supporting
rotor with said blade portion extending generally radially
therefrom, said attachment means comprising abutting, bonded
together radial inner ends of said shank rails;
at least one passage formed through said abutting, bonded together
ends of said shank rails; and
means extending between said shank rails adjacent the leading and
trailing edges thereof for closing the openings defined between
such edges and directing fluid from said shank rail passage to said
collar passage.
2. The structure of claim 1 further characterized in that said
blade portion includes a leading edge, a trailing edge, generally
airfoil shaped sidewalls extending therebetween, and an end closure
wall, said means for discharging coolant fluid from said cast
member chamber comprising a plurality of passages formed through
said trailing edge and said end closure wall.
3. The structure of claim 2 further characterized in that the
portion of said cast member chamber adjacent said trailing edge
passages contains a plurality of posts extending thereacross and
joining said blade side walls to thereby increase convective heat
transfer.
4. The structure of claim 1 further characterized in that said
insert includes means, integrally formed therewith, for
automatically establishing said spaced relationship between said
nozzles and said cast member.
5. A turbomachinery blade structure comprising:
a hollow, integrally cast member including a platform portion
adapted to define, in part, an inner boundary of a motive fluid
passage, a blade portion projecting from said platform portion, a
transition shank portion projecting from said platform portion
generally oppositely to said blade portion and defining an opening
to said hollow cast member, and a pair of juxtaposed shank rails
projecting from said transition shank;
a hollow insert slideably received within said hollow cast member
blade portion in spaced relationship thereto, said insert formed
with an open inner end for receiving a coolant fluid, a closed
outer end and a plurality of apertures for impinging said coolant
fluid against said cast member blade portion;
means for discharging said coolant fluid from said hollow cast
member blade portion;
means enabling attachment of said blade structure to a supporting
rotor with said blade portion extending generally radially
therefrom, said attachment means comprising a root insert extending
between and bonded to said shank rails, and said root insert formed
with at least one radially extending passage therethrough, said
hollow insert secured to said root insert with said hollow insert
open end in flow communication with said root insert passage;
and
means extending between said rails for closing said shank opening.
Description
This invention relates to gas turbine engines and more particularly
to an improved fluid cooled turbomachinery blade structure for use
in high temperature gas turbines.
It is well known that significant increases in gas turbine engine
performance, in terms of thrust or work output per unit of fluid
input, can be obtained by increasing the turbine inlet temperature
of the motive fluid or hot gas stream. It is also recognized that
one major limitation on turbine inlet temperature is that which is
imposed by the turbine blade temperature capability. In an effort
to extend turbine blade capability, numerous complex turbomachinery
blade structures have been proposed which employ one or more mode
of cooling using fluid usually extracted from the compressor.
In such blades, if a large percentage of the blade cooling is to be
derived from a cooling mode, such as film or transpiration cooling,
which is affected by the flow patterns of he hot gas stream over
the blade or by manufacturing tolerances, cooling effectivity is
difficult to predict.
Such prior blade structures have usually been complex in nature and
require sophisticated and expensive machining and assembly
techniques in their fabrication. In addition, many such prior blade
structures employ one or more brazed, welded, or similarly bonded
joints in the portion of the blade structure exposed to the hot gas
stream. As will be understood, such bonds may impose a severe
limitation on the operating temperature capacity of the blade and
such limitation will be greatly enhanced is such bond is operative
to transmit blade loading.
This invention, then, is concerned with a fluid cooled, high
temperature blade structure which overcomes the above mentioned
problems.
Accordingly, a primary object of this invention is a relatively low
cost, high temperature blade structure having all bonds spaced from
the portion of the blade structure in contact with the hot gas
stream.
Another object of this invention is a turbine blade structure
having predictable high temperature characteristics.
Other objects and advantages of the invention will become apparent
on reading the following description of the preferred
embodiment.
Briefly stated, the turbomachinery blade structure of this
invention comprises a cast member, means for mounting the cast
member to a supporting rotor, a insert for the cast member formed
with a chamber therein, and means for cooling said blade structure
by impingement of a cooling fluid on the inner surfaces of the
blade portion of the cast member. The cooling fluid is discharged
into the hot gas stream through trailing passages. All structural
bonds between the cast member, insert, and mounting means are
spaced from the hot gas stream.
While the specification concludes with claims particularly pointing
out and distinctly claiming the subject matter of this invention,
it is believed the invention will be better understood from the
following description of the preferred embodiments taken in
connection with the accompanying drawings wherein:
FIG. 1 is a partial cross-sectional view diagrammatically showing
one installation of the blade structure of this invention;
FIG. 2 is an exploded perspective view, in partial section, showing
one embodiment of the blade structure of this invention;
FIG. 3 is a cross-sectional view taken along line 3--3 of FIG.
2;
FIG. 4 is a cross-sectional view taken along line 4--4 of FIG.
2;
FIG. 5 is a partial cross-sectional view taken along line 5--5 of
FIG. 2;
FIG. 6 is a cross-sectional view, like that of FIG. 3, of another
embodiment of the blade structure of this invention;
FIG. 7 is a cross-sectional view taken along line 7--7 of FIG. 6;
and
FIG. 8 is a cross-sectional view taken along line 8--8 of FIG.
6.
LIke reference numerals will be used to refer to like parts and
features throughout the following description of the preferred
embodiment.
Referring now to the drawings and particularly to FIG. 1, the
turbine portion of a gas turbine engine has been shown
diagrammatically in partial section as comprising a rotor 10 having
a plurality of blades 12 extending radially therefrom around its
periphery. The blades 12 extend into a passage 14 through which a
motive fluid or hot gas stream (indicated by flow arrows in FIG. 1)
is directed and are adapted to extract energy from the motive fluid
and impart rotary motion to the rotor 10 in a well known manner. To
enable internal cooling of each blade 12, suitable means shown
generally at 16, may be provided to direct a coolant fluid
(indicated generally by the broken flow arrows in FIG. 1) through
the rotor 10 to each blade 12.
Turning now to FIGS. 2 through 5, one embodiment of the improved
blade structure of this invention has been shown as including a
hollow cast member 20, means 22 for engaging and securing the blade
to the supporting rotor 10, and an insert 24 for directing coolant
fluid within a blade portion 26 of the cast member 20.
The cast member 20 has been shown as including a platform portion
28, a blade portion 26 extending or projecting from the platform
portion 28, and a transition shank portion 30 extending from the
platform portion 28, generally oppositely to the blade portion 26,
and defining an opening or passage 32 to a chamber 34 within the
blade portion 26.
As best shown in FIGS. 2 and 4, the blade portion 26 is formed with
a leading edge 36, a trailing edge 38 and airfoil shaped side walls
40 extending therebetween which are suitably formed and adapted to
extract energy from the motive fluid flowing thereacross, as in
FIG. 1, through the mechanism of either action or reaction fluid
dynamics and impart rotary motion to the supporting rotor 10. The
chamber 34 is defined by blade side wall inner surfaces 42 and an
integrally cast end closure wall 44.
The cast member chamber 34 includes a railing edge portion 46
having a plurality of posts 48 extending thereacross and connecting
opposed side walls 40. A plurality of passages 50 are provided in
trailing edge 38 to enable efflux of coolant fluid from chamber 34
as will be hereinafter discussed. Additional efflux passages 52 may
be formed in end closure 44 to provide cooling to that area of the
blade.
The platform portion 28 has been shown as having a top surface 54
which is adapted to define, in part, the passage 14 into which the
blade portion 26 extends and through which the motive fluid or hot
gas stream is directed. The platform portion, as will be
understood, may be variously shaped to perform interlocking or
dampening functions between adjacent blades when arranged and
mounted in a circumferential row around the supporting rotor 10 as
in FIG. 1.
As previously indicated, the case member shank portion 30 is
integrally cast with and extends from platform portion 28,
generally oppositely of the blade portion 26, and defines the
opening or passage 32 communicating with cast member chamber
34.
In the embodiment of FIGS. 2 through 5 the means 22 for attaching
the blade to the rotor 10 has been shown as comprising juxtaposed
shank rails 56, integrally cast with member 20, which extend from
the shank 30 generally oppositely to blade portion 26. The rails 56
are suitably formed into abutting contact and suitably bonded
together as at 58. The outer surfaces of the joined shank rails 56
are suitably formed in a "fir tree," dovetail, or like
configuration, as shown generally at 60, so as to enable attachment
of the blade structure to the supporting rotor 10 in a well known
manner. A plurality of passages 62 are provided through the rail
abutment to enable influx of a coolant fluid to the blade structure
as will be hereinafter discussed.
The insert 24 has been shown as being a thin walled shell having
side walls 64 generally conforming to the contour of the blade side
walls 40 and formed with a plurality of nozzles or apertures 66
which are disposed in spaced relationship to the inner surfaces 42
of the blade portion 26 by suitable spacing means 68. As viewed in
FIG. 2, the insert 24 is closed at one end 70 and defines a chamber
72 therein which is open at end 74 to receive coolant fluid.
Suitable means as at 76 are provided to secure the insert 24 to the
cast member 20 in a manner enabling passage of coolant fluid into
chamber 72. In the embodiment of FIGS. 2 through 5 such means also
function to close passage 32 and comprise a collar 78 formed with a
passage 80 and a surrounding flange 82. The collar 78 is bonded to
the open end 74 of insert 24 with passage 80 communicating with
chamber 72 and the flange 82 abuts and is suitably bonded to a
lower rim 84 of the transition shank 30 in a manner securing the
insert 24 to the cast member 20 and closing passage 32.
In order to direct coolant fluid from passages 62 to collar passage
80 and, hence, into the insert chamber 72, suitable means such as
seal plates 86 are provided. As best shown in FIGS. 2 and 3, one
seal plate extends between rail leading edges 88 in overlapping
relationship with shank 30 and the rail abutment while the other
seal plate similarly extends between rail trailing edges 90.
Although the spacing means 68 has been shown as a plurality of
dimples, projections or the like, integrally formed with insert
side walls 64 and abutting inner surfaces 42 of the blade side
walls 40, it should be understood that such projections may be
carried by the cast member 20.
Referring now to the embodiment of FIGS. 6 through 8, the blade
attachment means 22 has been shown as comprising a root insert 92
which abuts and is suitably bonded to the opposed inner shank rail
surfaces 94 and 96. The insert 24 is secured at its open end 74
with chamber 72 communicating with passages 62. Like the mounting
means 22 of FIG. 2, the root insert 92 is suitably formed with a
"fir tree" or other suitable configuration, as at 60 and passages
62 are provided through the mounting means for delivery of coolant
fluid into the blade structure. In order to close passage 32, means
such as the seal plates 86 may be provided as in the embodiment of
FIG. 2.
As previously mentioned, a primary advantage of the turbomachinery
blade structure of this invention is the economical manner in which
it may be fabricated. For example, in the embodiment of FIGS. 2
through 5, the cast member 20, which includes the blade portion 26,
platform portion 28, transition shank 30 and rails 56, is formed as
a relatively non complex integral casting. The lower ends of shank
rails 56 are cast in a spaced apart, flared out position, as at 98
in FIG. 5, so as to allow insertion therebetween of the thin walled
insert 24. With the insert 24 bonded to the collar 78, this
assembly is simply inserted into cast member chamber 34, with means
68 automatically establishing the proper spacing between the insert
nozzles 66 and the blade inner surface 42. After the collar flange
82 is bonded to the shank rim 84, the ends of the shank rails 56
are suitably formed from their flared out position 98 into abutting
contact. The shank rails are then bonded at 58 and the proper
external contour, as at 60, is machined. The passages 62 are
preferably cast but may be machined after bonding.
The insert 24 may be economically formed of any suitable metallic
material by a deep drawing, stamping or like suitable process, with
the closed end 70 being either integrally formed with side walls 64
or bonded closed.
The embodiment of FIGS. 2 through 5 is also extremely advantageous
from the structural standpoint in that in transmitting either
centrifugal or aerodynamic loading to the support rotor 10 it is
not necessary to transmit force through a bonded joint. It should
also be noted that no bond is directly exposed to the high
temperature environment of the motive fluid and that all bonds are
arranged so as to be continually bathed in coolant fluid.
In the embodiment of FIGS. 6 through 8, the cast member 20 is
formed as an integral casting and is conveniently assembled with
the insert 24, after the latter has been secured to root insert 92,
by simply sliding insert 24 within the chamber 34 and bonding the
root insert 92 to inner rail surfaces 94 and 96. While enjoying the
structural advantages and fabrication economies of the embodiment
of FIGS. 2 through 5, the embodiment of FIG. 6 enables the material
selection of the blade portion 26 and the mounting means 22 to be
tailored to their respective environments, it being understood that
the stress loading and temperature environment of the blade portion
26 is somewhat different from the temperature environment and
structural loading of the mounting means 22.
In operation, the blade structure of this invention is mounted as
one of a circumferential row of blades in a well known manner to
the supporting rotor 10 by engaging the mounting means 22 with a
correspondingly contoured groove (not shown) in the rotor 10. The
blade portion 26 extends generally radially from the supporting
rotor and projects into the annular passage 14 through which the
motive fluid is directed. The blade portion 26, through the well
known mechanics of action and/or reaction fluid dynamics, extracts
energy from the hot gas stream and imparts rotary motion to the
supporting rotor 10. In performing this function, it is well known
that the efficiency, in terms of thrust or useful work output per
unit of fuel input, is greatly increased by increasing the turbine
inlet temperature of the motive fluid. To enable the blade
structure of this invention to operate in such a high temperature
environment and hence increase the efficiency of the turbomachinery
apparatus in which it is used, suitable means 16 are provided to
direct coolant fluid to inlet passage 62. From inlet passages 62,
the coolant fluid enters insert chamber 72 and is then impinged
against the blade wall inner surfaces 42 by nozzles 66. As will be
understood, the number, location and size of the nozzles 66 may be
varied so as to achieve a generally uniform side wall temperature
around the periphery of the blade.
From chamber 34, the coolant fluid is exhausted into the hot gas
stream through end closure passages 52 and trailing edge passages
50.
Posts 48 are provided in chamber portion 46 to increase the
convection heat transfer to the fluid passing into the hot gas
stream through trailing edge passages 50.
By exhausting the coolant fluid through passages 50 and 52,
disturbances to the flow of motive fluid and efficiency losses due
thereto are minimized. Further, by eliminating all blade side wall
passages, such as are common in film cooled blades, the structural
integrity of the blade is not jeopardized by high stress
concentrations due to mechanical voids and high localized
temperature gradients.
Since the blade structure of this invention does not rely on
transpiration, film or other like modes of cooling which may be
affected by the flow patterns of the motive fluid around the blade,
cooling effectivity and, therefore, the temperature capability of
the blade is highly predictable.
Accordingly, from the foregoing it will be appreciated that the
present invention provides an economically fabricated, non complex
cooled blade structure which possesses good and predictable high
temperature characteristics.
* * * * *