U.S. patent number 3,883,263 [Application Number 05/426,911] was granted by the patent office on 1975-05-13 for device for cooling rotor blades with solid profile of motor vehicle gas turbines.
This patent grant is currently assigned to Maschinenfabrik Ausburg-Nuremberg Aktiengesellschaft Werk Nuremberg. Invention is credited to Horst Mai.
United States Patent |
3,883,263 |
Mai |
May 13, 1975 |
Device for cooling rotor blades with solid profile of motor vehicle
gas turbines
Abstract
A device for cooling the twisted rotor blades with solid profile
of a motor ehicle gas turbines, according to which on or in the
support for the guiding device preceding the rotor part, nozzles
actuated by cooling air are so arranged that that part of the
turbine rotor which is adjacent to the active blade profile is
swept over by the cooling air. Also, the guiding device has that
part thereof which overlaps the ends of the rotor blades provided
with nozzle means acted upon by cooling air, said nozzle means
being so arranged that the cooling air flows off in radial
direction.
Inventors: |
Mai; Horst (Nuremberg,
DT) |
Assignee: |
Maschinenfabrik Ausburg-Nuremberg
Aktiengesellschaft Werk Nuremberg (Nuremberg,
DT)
|
Family
ID: |
5865048 |
Appl.
No.: |
05/426,911 |
Filed: |
December 20, 1973 |
Foreign Application Priority Data
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Dec 21, 1972 [DT] |
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2262597 |
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Current U.S.
Class: |
415/116;
415/117 |
Current CPC
Class: |
F01D
5/081 (20130101); F01D 11/10 (20130101) |
Current International
Class: |
F01D
11/08 (20060101); F01D 5/02 (20060101); F01D
5/08 (20060101); F01D 11/10 (20060101); F01d
025/08 () |
Field of
Search: |
;415/116,115,117,174
;416/92,95,96,97 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Raduazo; Henry F.
Attorney, Agent or Firm: Becker; Walter
Claims
What I claim is:
1. In combination with a gas turbine rotor of a motor vehicle
having a hub and twisted peripheral rotor blades with solid
profile, a guide wheel coaxially arranged with said rotor and
including: a central section extending around said hub, a
peripheral section extending around said rotor blades, and guide
blades interconnecting said central section and said peripheral
section, annular chamber means radially inwardly of said guide
wheel blades and provided with first nozzle means directed and open
toward that portion of said turbine rotor which is near to and
radially inwardly of said peripheral rotor blades, said annular
chamber means being adapted to be connected to a source of cooling
air, and second nozzle means provided in said peripheral section
and directed at least approximately radially toward the peripheral
portion of said peripheral rotor blades, said second nozzle means
being adapted to be connected to a source of compressed cooling
air.
2. An arrangement in combination according to claim 1 in which said
second nozzle means includes at least one annular slot.
Description
The present invention relates to a device for cooling twisted rotor
blades with solid profile of motor vehicle gas turbines, according
to which on, or in the support for the guiding device preceding the
rotor part, nozzles actuated by cool air are so arranged that that
part of the turbine rotor which is adjacent to the active blade
profile is swept over by cooling air.
The increase in the gas temperature at the turbine entrance desired
with gas turbines in order to obtain an increase in the output and
in the thermal degree of efficiency is limited by the material
available for turbine wheels and turbine blades. The temperature
limit of these materials is at present at approximately
950.degree.C for turbines with reasonable life span. In order to
increase the gas temperature at the turbine entrance, it has been
suggested with a heretofore known motor vehicle gas turbine to
cause cooling air to act upon the blade base or that part of the
turbine rotor which is adjacent to the active blade profile while
by heat conduction heat from the blade body was continuously
conveyed to the blade base and from there to the cooling air. While
with this heretofore known construction it is possible to reduce
the temperature at the blade base to a considerable extent, the
temperature at the blade head is still relatively high so that also
the medium blade temperature (equaling one-half times the blade
head temperature, plus the blade base temperature) still remained
relatively high.
It is, therefore, an object of the present invention to provide a
blade cooling device by means of which it will be possible at a
predetermined gas temperature at the turbine entrance to realize an
as low as possible medium blade temperature. This object and other
objects and advantages of the invention will appear more clearly
from the following specification, in connection with the
accompanying drawings, in which:
FIG. 1 is a longitudinal section through a rotor of a vehicle gas
turbine and through a portion of the guiding device.
FIG. 2 illustrates a section taken along the line II--II of FIG. 1
and shows a development of the rotor and guide wheel.
The device according to the present invention for cooling the rotor
blades with solid profile of motor vehicle gas turbines is
characterized primarily in that also the guiding device has that
portion thereof which overlaps the rotor blade ends provided with a
nozzle device adapted to be actuated by cooling air while the
nozzles are so arranged that the cooling air flows out in radial
direction. Inasmuch as a cold air ring forms around the blade ends,
it will be appreciated that with the cooling device according to
the invention, in addition to the drop in temperature from the
blade center to the blade base there also exists a drop in
temperature from the blade center to the blade head so that the
medium rotor blade temperature (equal turbine entrance temperature
assumed), is lower than the medium rotor blade temperature of
heretofore known turbine rotors with exclusive blade base cooling,
so that in conformity with the present invention the life span of
the rotor blades is considerably increased. A further advantage of
the cooling device according to the invention consists in that the
cooling air reduces the loss in working gas through the gap
provided between the rotor blade ends and that portion of the
guiding device overlapping the latter.
In order to avoid siren-like noises in the rotor part due to the
provided nozzles in that part of the guiding device which overlaps
the blade ends, it is suggested according to a further feature of
the invention to design the nozzles as one or more annular
slots.
Referring now to the drawings in detail, the arrangement shown
therein comprises a rotor 1 of a motor vehicle gas turbine of the
axial type, said rotor having a hub 2, a wheel body 3, and the
rotor blades 4. The blades 4 are twisted in the heretofore
customary manner and while being thin-walled have a solid profile.
The rotor 1 is provided by a guiding device 5 with guiding blades
6. The outer guiding blade ring 7 continues in the direction toward
the rotor 1 while being correspondingly reinforced and overlaps the
rotor. Between the ends of the rotor and the inner wall of the
outer guiding blade ring extension 8, there is an axial gap S
having a width of, for instance, 0.5 mms. The extension 8 which is
coaxial with the rotor 1 has that part thereof which overlaps the
rotor provided with annular slots 9 directed perpendicularly with
regard to the rotor axis. The slots 9 communicate through a conduit
10 with a nonillustrated source of compressed cooling air. As
cooling air may be employed a portion of the air compressed by the
compressor of the gas turbine. Expediently, however, if as cooling
air there is employed the compressed air which is considerably
cooler than the compressor air and is fed directly by the
compressed air storage container to the slots 9.
In a heretofore known manner, an additional cooling device is
arranged in the part 12 of the guiding device 5. This last
mentioned cooling device serves for cooling the blade base. The
cooling device comprises a plurality of nozzles 13 which, through
an annular chamber 14, are in communication with a source of
compressed air (not illustrated).
The cooling air for the rotor blade ends flows under pressure from
the slots 9 radially inwardly toward the ends of the rotor. The
curvature of the rotor blades 4 brings about on one hand a
conveying of the cooling air in a direction counter to the
direction of flow of the working gas and on the other hand the flow
of working gas brings about a conveying of the air in the direction
of the working gas. Inasmuch as the cooling air is specifically
heavier than the working gas, due to the centrifugal force, a cold
air ring remains around the blade ends. In view of this cool air
zone, a temperature drop toward the blade ends is created. Since,
in view of the cooling of the blade base there exists also a
temperature drop toward the base of the blades, heat is conveyed
radially inwardly and also radially outwardly.
It is, of course, to be understood that the present invention is,
by no means, limited to the specific showing in the drawings, but
also comprises any modifications within the scope of the appended
claims.
* * * * *