U.S. patent number 3,706,508 [Application Number 05/134,601] was granted by the patent office on 1972-12-19 for transpiration cooled turbine blade with metered coolant flow.
This patent grant is currently assigned to Curtiss-Wright Corporation. Invention is credited to William Lingwood, deceased, Seymour Moskowitz.
United States Patent |
3,706,508 |
Moskowitz , et al. |
December 19, 1972 |
TRANSPIRATION COOLED TURBINE BLADE WITH METERED COOLANT FLOW
Abstract
A turbine stator blade having a porous skin covering a strut
member with channels for cooling air fed from the root, and a
removable metering plate attached to the root and having orifices
of various sizes for transmitting air to the blade channels, the
metering plate being selected for having appropriate orifices for
the cooling requirements of blades in differing temperature and
pressure environments.
Inventors: |
Moskowitz; Seymour (Fort Lee,
NJ), Lingwood, deceased; William (LATE OF Watchung, NJ) |
Assignee: |
Curtiss-Wright Corporation
(N/A)
|
Family
ID: |
22464103 |
Appl.
No.: |
05/134,601 |
Filed: |
April 16, 1971 |
Current U.S.
Class: |
415/115; 416/96R;
416/231R; 416/97R; 416/96A; 416/97A |
Current CPC
Class: |
F01D
5/3038 (20130101); F01D 5/183 (20130101); F01D
5/147 (20130101) |
Current International
Class: |
F01D
5/18 (20060101); F01d 005/18 () |
Field of
Search: |
;416/90,92,95-97
;415/114,115 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Powell, Jr.; Everette A.
Claims
What is claimed is:
1. In a gas turbine engine having circumferential temperature
gradients and having a ring of circumferentially disposed stator
blades having different cooling requirements at different
circumferential locations, the combination comprising a
transpiration cooled stator blade having a strut member of
generally airfoil configuration having on the surface thereof a
plurality of lands, a porous skin sheathing the strut and defining
with the lands a plurality of discrete coolant passages, the strut
having a root portion integral therewith mountable at any portion
of the blade ring, the root having a plurality of apertures
therethrough each communicating with an associated blade coolant
passage, an interchangeable metering plate detachably attached to
the root on the side opposite the strut, the metering plate having
a plurality of metering orifices therethrough congruent with the
strut apertures for metering a supply of coolant to each blade
passage, each plate being selected to pass an amount of coolant to
its associated blade in accordance with the coolant requirement of
the blade at its respective circumferential location.
2. The combination recited in claim 1, wherein the metering
orifices of each plate are of various sizes to pass different
amounts of coolant in accordance with the coolant requirements of
their respective blade passages.
3. The combination recited in claim 2, wherein the root apertures
are generally funnel-shaped with their entrance ends facing the
orifices of the metering plate and of larger size than any metering
orifice, the other ends of the root apertures opening into their
respective blade passages and having approximately the same shape
and cross-section as their respective blade passages.
4. The combination recited in claim 3, wherein the lands on the
strut are generally longitudinally disposed and the direction of
the flow path is generally from the metering plate toward the blade
tip.
Description
BACKGROUND OF THE INVENTION
The invention herein described was made in the course of or under a
contract with the Department of the Air Force.
This invention relates to stator blades for gas turbines, and more
particularly to such blades having a porous skin and internal
passages to which cooling air is fed to bleed through the skin to
provide a cooling action during operation of the blade in the flow
of the combustion gases of the turbine, with particular reference
to blades wherein it is desired to feed different amounts of
coolant to portions of the skin which may be exposed to different
temperatures and gas pressures than adjacent portions.
In U. S. Pat. No. 3,402,914 there is shown a blade having a
structural spar with longitudinal air channels on its surface fed
from the root, with the air bleeding through a porous skin to cool
the blade. Some control of the distribution of air coming through
the skin has been achieved by masking portions of the skin with
flame-sprayed metal powder to diminish the permeability of the
skin. Such a blade is very expensive to fabricate, and control of
the degree of permeability desired is very difficult. The blade has
the further disadvantage that once fabricated, no further control
is possible. In a gas turbine engine there are circumferential
gradients of temperature as well as chordwise and lengthwise of the
blade, owing to uneven distribution of fuel and the presence of
supporting struts at various locations which partially occlude or
redistribute the flow of combustion gases. Also, the flow of
coolant air to the blades may be nonuniform, owing to varying
degrees of intricacy in the flow path the air must follow to reach
the various blades, or to their varying distances from the source
of cooling air. The blade of the patent has no provision for
feeding its air channels with different amounts within a single
blade, and since all blades are the same in a given engine they are
unevenly adapted to different circumferential locations.
U. S. Pat. No. 3,240,468 displays a different approach to the
problem. The blade of this patent has a hollow strut having on its
surface longitudinal and transverse lands defining discrete cells
under the porous skin. Coolant is fed to the interior of the hollow
strut, and each cell has an aperture communicating with the strut
interior, which apertures may be of various sizes whereby different
amounts of coolant may be supplied to different cells. This blade,
again, is expensive to fabricate, and also has the same
disadvantage that once finished no changes may be made, so that all
blades in a given engine are alike. Therefore, no provision can be
made to accommodate circumferential gradients of temperature, and
the blades are not equally well adapted to all locations in the
engine. The blades are designed for the hottest spots in the
engine, requiring the most coolant flow. Such a procedure wastes
cooling air which is bled from the compressor, and depresses engine
performance.
SUMMARY
The blade of the present invention provides coolant channels of
different cross-sections distributed across the chord of the blade,
in order to accommodate both temperature and pressure gradients
across the chord. The limitations of the prior art are overcome by
providing metering means at the base of each blade whereby a
selected amount of coolant can be fed to each blade passage. The
metering means being removable and replaceable, when parameters
have been established for cooling requirements at various locations
an appropriately selected metering means can be attached to each
blade. The blades themselves being of simpler construction than
those of the prior art, they are better adapted to quantity
production, and the metering means being positioned at the root of
the blade out of the gas stream, it may be formed of less critical
and more easily worked material, and hence is susceptible of easy
reworking or stocking quantities of metering plates of varying
coolant distributing characteristics. In servicing an engine
employing this invention the blades may be reassembled in any
order, if the appropriate metering plate for a given location is
used. Thus, it is possible to provide a single blade design adapted
to any location in an engine, whatever the temperature and pressure
variations and concomitant cooling requirements, without expensive
modification of individual blades.
It is an object of this invention to provide a means of metering an
appropriate amount of coolant to selected portions of a turbine
stator blade.
It is another object to provide means of metering coolant
appropriately to stator blades in different circumferential
locations in an engine.
A further object is the provision of turbine stator blades adapted
to quantity production, in combination with low cost metering means
for each blade whereby any blade is suitable for any location in an
engine.
Other objects and advantages will become apparent on reading the
following specification in connection with the accompanying
drawing.
BRIEF DESCRIPTION OF THE DRAWING
FIG. 1 is an exploded view of an elevation of the blade and
metering means of the invention;
FIG. 2 is a view of the root of the blade taken on line 2--2 of
FIG. 1;
FIG. 3 is a bottom view of the metering plate to be attached to the
blade;
FIG. 4 is a cross-section of the blade taken on line 4--4 of FIG.
1; and
FIG. 5 is a fragmentary elevational cross-section taken on line
5--5 of FIG. 4.
DESCRIPTION OF THE PREFERRED EMBODIMENT
FIG. 1 shows the concave or pressure side of a stator blade 11. The
blade has a structural spar or strut member 12 of generally airfoil
configuration, which may be either solid as shown or cored out
hollow to reduce weight. The strut has on its surface a plurality
of generally longitudinal lands 13, and is sheathed in a porous
skin 16 of one of the types well known in the art, such as a metal
mesh pressed and sintered to the desired degree of porosity. The
skin is welded, brazed, diffusion bonded, or otherwise suitably
attached to the strut at the tip and root portions and along the
lands 13, and defines with the land a plurality of coolant passages
14 which are discrete from each other. Although in the embodiment
shown, the lands 13 and passages 14 are straight, they may when
required be curved.
The blade has a root portion 17 integral with the strut and
appropriate for mounting the blade in an engine. In the base of the
root, opposite the side from which the strut extends, is provided a
recess 18 in which may be installed a metering plate as described
below. The root has generally funnel-shaped feeder apertures 19
therethrough (best shown in FIGS. 2 and 5) communicating with
passages 14, with the larger portion of the funnel opening on the
base side and fairing into a slit on the strut side, each slit
opening into its associated coolant channel and being of
approximately the same cross-section as the channel. Where space is
restricted, a single root aperture may feed two blade channels. The
pressure and suction sides of the blade may have different numbers
of coolant passages 14, and the passages may be of different sizes,
depending on the cooling requirements at any particular location.
When the coolant passages are of different sizes, the feeder
apertures 19 may also vary correspondingly, so that larger amounts
of coolant may be fed to larger channels.
A metering plate 21 is installed in recess 18 of the blade root,
held thereto by screws 22 or other suitable means. There may be a
gasket 23 disposed between the metering plate and the blade root to
prevent circumferential leakage of cooling air, although if the
surface of recess 18 is machined with a smooth surface no gasket is
necessary.
The metering plate 21 (shown in FIG. 3) has a plurality of metering
orifices 24 therethrough, disposed in a configuration congruent
with the funnel-shaped root apertures 19. Orifices 24 are of
various sizes, in accordance with the amount of cooling air to be
metered to the corresponding blade passages, and one orifice may be
used to feed two blade passages. The pattern of larger and smaller
orifices 24 shown in FIG. 3 is not necessarily that of any given
engine, but is thus shown only for purposes of illustration.
The leading edge of the blade is commonly the hottest portion and
may therefore require the greatest flow of coolant. The blade strut
may be provided with a nose portion at the leading edge, as shown
in FIG. 4, which channels the coolant at that portion into discrete
passages on the concave and convex sides of the blade, or the strut
nose may be omitted and all the coolant at the leading edge may
flow through a single channel.
The orifices 24 have a smaller cross-section than their
corresponding apertures 19, and also smaller than the summative
cross-section of the capillary porosity of the skin overlying any
corresponding blade passage. Hence, orifices 24 constitute the
governing restriction in the coolant path, and determine how much
air will flow to any blade passage, in accordance with the cooling
requirement at that location. The ratio of orifice cross-section to
blade passage cross-section will never be greater than 1:1, and
will be that large only in an occasional instance where no
restriction is desired for the coolant flow to a given passage. No
specific rule can be given for an optimum ratio, since the amount
of restriction is a variable design consideration for each type of
engine, for the location of a blade in the engine, and for specific
passages in a blade. However, the ratio commonly lies somewhere in
the range from 0.5:1 to 0.1:1.
The bulk of the metering plates are fabricated according to the
cooling requirements of the generality of blades in a given engine.
When the distribution of cooling for a specific blade differs
because of the circumferential gradients of temperature and
pressure brought about by the factors previously discussed, it is
easy to provide a plate adapted to that blade.
If more coolant is needed for one or more passages, the
corresponding orifices may be reamed out to the suitable size.
Since the metering plate is made of readily workable metal, such as
low alloy steel, for instance, this procedure is far simpler and
cheaper than attempting to enlarge an aperture in the blade itself.
Blades for high performance turbines are made of hard, tough, high
temperature alloys which are machinable only with great difficulty
and consequent expense in time, tool breakage, and low production.
Further, in the blade material it is difficult to hold small
tolerances, so that in small bores such as of the order of
one-sixteenth inch or less in diameter, a departure of a few
thousandths of an inch from the specified size results in a very
marked percentage change in cross-sectional area.
If it is found that less air is needed at some blade locations, or
for some blade passages, the corresponding metering plate may
either have one or more orifices plugged and rebored, or a new
plate may be installed with appropriate orifices.
* * * * *