U.S. patent number 3,885,609 [Application Number 05/324,780] was granted by the patent office on 1975-05-27 for cooled rotor blade for a gas turbine.
Invention is credited to Oskar Frei, Dilip Mukherjee.
United States Patent |
3,885,609 |
Frei , et al. |
May 27, 1975 |
**Please see images for:
( Certificate of Correction ) ** |
Cooled rotor blade for a gas turbine
Abstract
The rotor blade body has a first flow path extending parallel to
and immediately downstream of the blade front. This path passes
through a trough-shaped indentation in the blade tip before
terminating in an air exit in the zone of the trailing edge. One or
more secondary flow paths also pass through the blade body and
terminate in the zone of the trailing edge. These secondary flow
paths reverse the flow either by 90.degree. or 180.degree. and are
of larger intermediate flow cross-sectional area. Restrictors can
be provided in the exits for the secondary paths to obtain high
exit velocities.
Inventors: |
Frei; Oskar (8404 Winterthur,
CH), Mukherjee; Dilip (8400 Winterthur,
CH) |
Family
ID: |
4193074 |
Appl.
No.: |
05/324,780 |
Filed: |
January 18, 1973 |
Foreign Application Priority Data
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Jan 18, 1972 [CH] |
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00698/72 |
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Current U.S.
Class: |
416/97R;
415/115 |
Current CPC
Class: |
F01D
5/187 (20130101); F01D 5/20 (20130101); F05D
2240/126 (20130101) |
Current International
Class: |
F01D
5/18 (20060101); F01D 5/14 (20060101); F01D
5/20 (20060101); F01d 005/18 () |
Field of
Search: |
;416/92,95-97
;415/115-116 |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
Primary Examiner: Powell, Jr.; Everette A.
Attorney, Agent or Firm: Phillips, Moore, Weissenberger,
Lempio & Strabala
Claims
What is claimed is:
1. A cooled rotor blade for a gas turbine comprising
a one-piece rotor blade body having a blade front, a trailing edge
and a blade tip at one radial end extending from said blade front
to said trailing edge, said blade tip having a trough-shaped
indentation extending longitudinally therein;
means defining a first flow path through said blade body extending
immediately downstream of and parallel to said blade front and
terminating in said trough-shaped indentation;
a first coolant exit in said blade body in the zone of said
trailing edge, said exit being in communication with said
trough-shaped indentation on the suction side of said body for the
passage of coolant therethrough; and
means defining a second flow path and a third path through said
blade body, each of said second and third flow paths having a
portion parallel to said first flow path and including portions for
deflecting respective flows of coolant 90.degree. therein; a second
coolant exit in communication with said second flow path and a
third coolant exit in communication with said third flow path, each
of said second and third coolant exits being disposed over a part
of the height of said blade body in the zone of said trailing edge
on the pressure side of said body.
2. A cooled rotor blade as set forth in claim 1 wherein each of
said second and third flow paths have boundary walls defining
portions of said respective flow paths and wherein fins are
disposed on said walls projecting into said respective second and
third flow paths.
3. A cooled rotor blade as set forth in claim 1 which further
comprises means in each of said second and third exits for
throttling the flow of coolant therefrom.
Description
This invention relates to a cooled rotor blade for a gas
turbine.
Generally, in order to achieve cooling of the rotor blades, both
guide blades and rotor blades, in an operating turbine, two
contradictory conditions must be basically satisfied. First, good
cooling requires high coefficients of heat transmission which, in
turn, involve high flow velocities and relatively high pressure
losses. Second, the amount of cooling air required by each blade
should be as small as possible because the cooling air branched
off, for example, from a compressor represents a loss in a certain
sense and results in a deterioration of the efficiency of the
entire process. Moreover, in practice it frequently occurs that the
pressure gradient available between the cooling air entry into the
blade and the cooling air exit from the blade is relatively low.
Thus, the required velocities cannot be obtained or, if obtained
because a high consumption of cooling air can be tolerated, is done
only with difficulty.
In order to overcome these basic problems, it has been known to
provide constructions in which the cooling air is passed once
through the blade through a plurality of ducts radially of the
machine from the interior to the exterior. The required velocities
can be easily obtained with this system but require relatively
large quantities of air. Moreover, the cooling capacity of the air
in this system is only very incompletely utilized.
It has also been known to provide rotor blades which have shroud
bands with labyrinth projections in a gap between the casing in
which the rotor blades are installed and the blade tips in order to
reduce gap losses. If these blades are cooled in the manner
described above, the cooling air is discharged into the inner
cavity of the shroud band after flowing through the individual
blades in the radial direction before being discharged rearwardly
in the same direction as the working gas.
Accordingly, it is an object of the invention to achieve an optimum
cooling of rotor blades with a relatively low consumption i.e. a
small quantity of cooling air and a relatively low available
pressure gradient.
It is another object of the invention to provide a rotor blade of
cast construction which can be cooled effectively.
Briefly, the invention provides a rotor blade having a blade front
or nose, a trailing edge and a blade tip at one radial end with a
coolant flow path located immediately downstream of and parallel to
the blade front or nose which terminates in a trough-shaped
indentation in the blade tip. In addition, a coolant exit is
provided at the end of the indentation on the suction side of the
blade body in the zone of the trailing edge.
The trough-shaped indentation, whose air exit on the trailing edge
has a relatively large exit cross-section, enables the low pressure
prevailing at the trailing edge of the blade to be transposed
practically directly to the end of the flow path so that the entire
pressure gradient is available for this relatively short distance.
By contrast to known constructions, this results in increased
velocities and therefore better coefficients of heat transfer. A
further advantage of the construction is due to the fact that the
provision of the air exit on the suction side of the blade allows
the maximum available pressure gradient to be utilized for cooling
the blade front. The maximum duct velocity, at the minimum cooling
duct cross-section, and therefore the maximum cooling effect may
thus be produced with a given amount of cooling air. The entire
pressure gradient is thereby available for the actual cooling
section in the aforementioned rotor blades with shroud bands. In
this known construction, however, all the disadvantages associated
with a shroud band, such as an additional mass which is subject to
centrifugal forces and as a result imposes a substantial load on
the blade root, must be tolerated. Furthermore, in this known
construction it is not possible to transfer the lowest pressure
prevailing on the suction side of the blade onto the end of the
flow path. A further disadvantage of the known construction is due
to the increased manufacturing costs because blades with a shroud
band cannot be produced as an integral casting i.e. as a one-piece
casting.
While the above described flow path particularly cools the blade
front, two possibilities are available for cooling the remaining
parts of the blade. To this end, means are provided to define a
second flow path which extends parallel to the first flow path and
leads to an air exit in the zone of the trailing edge. The exit for
this flow path extends over the height of the blade and is located
downstream of a reversal in the flow path through which the flow
can be reversed 180.degree.. In the other case, a second and third
flow path are provided, parallel to the first flow path in the
blade, in order to lead the air to exits after being deflected
through 90.degree.. In this case, each of the exits for the
secondary flow path cover a part of the blade height and are
disposed in the zone of the trailing edge. Which of the two
possibilities is more favorable must be determined in relation to
the circumstances governing the individual case, for example, in
accordance with the amount of heat to be dissipated, the available
pressure gradient and the blade length. connection, have
Dividing the air over the two or three flow paths may be
advantageously performed by means of restrictors in the air exits
of the second and third flow paths. These restrictors can also be
adapted for individual adjustment on the basis of tests. In this
connection, it is advantageous if the second and thirid flow paths,
have a flow with the least possible losses as far as the
restrictors and if, practically, the entire nominal pressure
gradient occurs at the restrictor positions of the aforementioned
flow paths.
If any adequate pressure gradient is available for the second and
third flow paths, it will be advantageous to provide the air exits
thereof on the delivery side of the blade because flow discharge on
this side is more advantageous and simpler in terms of flow. By
contrast, the provision of the aforementioned air exits on the
suction side will provide a better cooling action because, on the
one hand, a higher pressure gradient is available which enables
higher velocities and higher thermal transfer coefficients to be
achieved while, on the other hand, film cooling on the suction side
is more effective because of the higher thermal transfer
coefficients on the suction side. This film cooling is known to be
the result of the cooling air which flows along the surface of the
blade.
It is, of course, also possible to provide the air exits in the
trailing edge itself.
To achieve a further improvement of heat dissipation, it may be
advantageous if the second and third flow paths have boundary walls
at least over a part of their length which are provided, at least
partially, with fins.
It is generally known that cast blades are preferable to forged and
welded blades more particularly because of their higher
high-temperature resistance, their materials and because of the
greater simplicity of manufacture or because of the absence for any
need of finish-machining. The blade of the invention is therefore
advantageously constructed so that the blade represents a precision
casting in its entirety i.e. the blade is a one-piece casting.
These and other objects and advantages of the invention will become
more apparent from the following detailed description and appended
claims taken in conjunction with the accompanying drawings in
which:
FIG. 1 illustrates a longitudinal sectional view taken on line I--I
of FIG. 2 of a rotor blade according to the invention;
FIGS. 2 and 3 illustrate views taken on line II--II and III--III of
FIG. 1, respectively;
FIG. 4 illustrates a sectional view taken on line IV--IV of FIG.
3;
FIG. 5 illustrates a plan view of the rotor blade of FIG. 1 taken
in the direction of the arrow A in FIG. 1;
FIG. 6 illustrates a plan view of the rotor blade of FIG. 7 in the
direction of the arrow A of FIG. 7;
FIG. 7 illustrates a longitudinal sectional view taken on line
VI--VI of FIG. 8 of a second embodiment of a rotor blade according
to the invention;
FIG. 8 illustrates a sectional view taken on line VII--VII of FIG.
7; and
FIG. 9 illustrates a detail view of a modification of the
construction shown in FIG. 8.
Referring to FIG. 1, the cooled rotor blade is disposed to move in
a flow duct 1 indicated by an outer filler ring segment 4 of a
casing (not shown) and which receives flow from the right (arrow B)
as viewed. The rotor blade is secured in a rotor ring which is
screened relative to the duct 1 by heat exchange segments 5 which
provide protection against hot gases. The heat exchange segments 5
in the same way as the filler ring segment 4 comprise material of
high-temperature resistance while the ring is constructed of less
expensive ferritic material.
The rotor blade is made of one-piece construction and has three
separate parallel flow paths for a coolant such as cooling air
which extend from an aperture 8 disposed in the blade root and fed
with cooling air by channels. The first relatively narrow flow duct
9 extends parallel to and directly downstream of the blade front or
nose 10. The duct 9 also extends into a trough-shaped indentation
11 at the blade tip. The indentation 11 communicates with a
relatively wide air exit 12 on the suction side of the blade in a
socket 13 (FIG. 5) which surrounds the air exit 12 in the manner of
a wall following the blade profile contour. The flow cross-section
of the indentation 11 and of the air exit 12 are broad. This means
that the pressure at the duct end 14 is low because the gas-side
pressure at the suction side of the trailing edge 17 comes into
effect practically at the duct end 14. The entire pressure gradient
between the aperture 8 and the flow duct 1 on the suction side of
the trailing edge 17 of the blade may thus be utilized for cooling
the particularly hot front of the blade.
Second and third flow paths 15 and 16 are provided which are less
direct and in this example, while being simultaneously deflected
through 90.degree., extend from the aperture 8 to air exits 19, 20
in the zone of the traling edge 17. The second flow path 15,
separated from the third flow path 16 by a bulkhead 18, cools the
trailing edge 17 of the outer zone of the blade while the third
path 16 supplies the inner part of the trailing edge 17, closer to
the blade root, with cooling air.
In the blade illustrated in FIG. 1, the air exits 19, 20 are
disposed on the delivery side of the blade so that the flow
conditions are improved. It is, of course, also possible to dispose
the air exits 19, 20 on the suction side of the blade if it is
necessary to utilize the maximum available pressure gradient in
order to achieve adequate cooling of the trailing edge (see FIG.
8). For the sake of completeness, it should be mentioned that the
air exits 19, 20 may also be disposed in the trailing edge itself
(FIG. 9). In order to improve the cooling action, it is also
possible to provide the flow paths 15, 16 with cooling fins, at
least over a part of the boundary walls defining the paths but this
is not separately shown.
The flow paths 15, 16 are constructed so that flow therethrough as
far as the air exits 19, 20 takes place at relatively low
velocities and therefore substantially without pressure loss. The
terminology "practically without pressure loss" means that the
second, and on occasion, the third flow path in the middle part of
the blade is constructed, relative to the quantity of cooling air
flowing through, so that the pressure produced by centrifugal force
at least approximately compensates the flow resistance as far as
the radially outer deviation. The aforementioned available pressure
gradient is therefore almost entirely consumed in the air exits 19,
20. To this end, the air exits 19, 20 are provided with restrictor
and guide elements 21, 22 so that the air distribution in the air
exits 19, 20 is at least approximately uniform over the blade
height, accompanied by high flow velocities and therefore large
coefficients of heat transfer. All these features result in uniform
and good cooling of the trailing edge 17 of the blade with
relatively small quantities of cooling air and with relatively low
available pressure gradients.
Distribution of the air over the three different flow paths may be
varied to some extent by varying the restrictor and guide members
21, 22. This distribution must be defined from case to case and
depends on given conditions, for example flow, pressures, given
temperature and their distribution.
Referring to FIG. 7, the rotor blade can also be constructed
without the need of the third flow path. As shown, apart from the
inflow from the left (arrow C) such a rotor blade differs from the
blade described in FIG. 1 by the absence of the third flow path 16.
Also, the second flow duct 15 incorporates a reversal through
180.degree.. To this end, the flow duct 15 initially extends
radially outwardly in the middle part of the blade and then leads
through a reversal chamber 23 through 180.degree. into a second
portion 25 disposed over the entire height of the blade to return
to the blade root. The two part flow paths 15, 25 are separated
from each other by a bulkhead 24. In this embodiment, the second
flow path is subject to low pressure losses, at least as far as the
reversal. Thus, practically the entire gradient is available for
uniformly distributed discharge on the trailing edge over the
entire height of the blade, a feature which cannot readily be
achieved against the action of centrifugal force. As shown in FIG.
6, the blade tip is of similar construction as above a indicated by
like reference characters.
The embodiment of FIG. 7 which involves more difficulties for the
uniform distribution of the second stream of cooling air is
suitable more particularly for smaller machines with blades of
lower height and for machines with a lower peripheral velocity.
Both embodiments (FIGS. 1 and 7) are advantageously produced as
separate castings by the precision casting method so that in
addition to the advantages already mentioned, it is possible to
utilize the advantages of cast as against forged blades.
* * * * *