U.S. patent number 3,795,458 [Application Number 05/218,161] was granted by the patent office on 1974-03-05 for multistage compressor.
This patent grant is currently assigned to Brown Boveri-Sulzer Turbomachinery Limited. Invention is credited to Rene Strub.
United States Patent |
3,795,458 |
Strub |
March 5, 1974 |
MULTISTAGE COMPRESSOR
Abstract
The axial-flow low pressure section and radial-flow or
diagonal-flow high pressure section are separated by a recooler in
which the working fluid is first deflected outwardly from the
rotor, spread fanwise in a channel around and perpendicularly of
the rotor, then deflected towards the rotor and fed perpendicularly
through a channel to the compressor axis. In addition, a cooling
element is disposed in one of the channels for cooling of the
working fluid.
Inventors: |
Strub; Rene (Winterthur,
CH) |
Assignee: |
Brown Boveri-Sulzer Turbomachinery
Limited (Zurich, CH)
|
Family
ID: |
4196520 |
Appl.
No.: |
05/218,161 |
Filed: |
January 17, 1972 |
Foreign Application Priority Data
Current U.S.
Class: |
415/149.2;
415/179; 415/143 |
Current CPC
Class: |
F04D
17/025 (20130101); F04D 29/5826 (20130101) |
Current International
Class: |
F04D
29/58 (20060101); F04D 17/02 (20060101); F04D
17/00 (20060101); F04d 015/00 (); F04d 027/00 ();
F04d 029/58 () |
Field of
Search: |
;415/177,178,179,149 |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
Primary Examiner: Raduazo; Henry F.
Attorney, Agent or Firm: Kenyon & Kenyon Reilly Carr
& Chapin
Claims
1. A multistage compressor comprising
a casing;
a rotor within said casing;
an axial-flow low-pressure section having a plurality of stages
about said rotor for compressing a working fluid without cooling to
a maximum permissible temperature;
a radial-flow high-pressure section downstream of said low-pressure
section on said rotor;
means within said casing between said low-pressure section and said
high pressure section including a first deflector section for
deflecting the working fluid perpendicularly outwardly away from
said rotor, a first channel for thereafter spreading out the
working fluid flow fanwise around and perpendicularly to said
rotor, a second deflector section for deflecting the fluid
perpendicular to said rotor towards said rotor and thereafter into
said high-pressure section; and
at least one cooling element in said means for cooling the working
fluid passing through said means to reduce the heat of compression
acquired by the flow in said axial-flow section and to achieve a
very high compression
2. A multistage compressor as set forth in claim 1 wherein said
cooling
3. A multistage compressor as set forth in claim 1 wherein said
stages includes axial flow blades for compressing the working fluid
without
4. A multistage compressor as set forth in claim 3 wherein said
blades of
5. A multistage compressor as set forth in claim 5 wherein at least
one stage downstream of said adjustable blades includes
non-adjustable blades.
6. A multistage compressor as set forth in claim 1 wherein said
high-pressure section includes at least two radial-flow rotors and
a second cooling element between said radial flow rotors for
cooling the
7. A multistage compressor as set forth in claim 1 which further
includes an adjustable exit guide blade downstream of said stages
of said low-pressure section and a non-adjustable entry guide blade
between said exit guide blade and said means.
Description
This invention relates to a multistage compressor.
Heretofore, multistage compressors have been known to have a rotor
on which an axial-flow low-pressure section is disposed with stages
for compressing a working fluid without cooling to a maximum
permissible temperature. The low-pressure section has been followed
by a radial-flow (or diagonal-flow) high-pressure section while a
recooler has been disposed in the fluid flow path between the
low-pressure section and high-pressure section. Compressors, of
this kind are known, for instance from Motortechnische Zeitschrift,
Jahrgang 13, Nr. 2, February 1952.
However, these known compressors have been of relatively long
dimensional lengths. As a result, such has resulted in excessive
whirling. Also, the number of radial-flow stages has been
limited.
Accordingly, it is an object of the invention to provide a
compressor of very small dimensions.
It is another object of this invention to reduce whirling in a
compressor.
It is another object of this invention to be able to use two or
more consecutive radial-flow stages without axial reversal of the
working fluid.
Briefly, the invention provides a multistage compressor having a
rotor, an axial-flow low-pressure section and a radial-flow high
pressure section with a means for deflecting a working fluid
leaving the low-pressure section first away from the rotor and then
towards the rotor for entry perpendicularly into the radial-flow
high pressure section as well as a cooling element for cooling the
working fluid flowing into the high-pressure section. The means for
guiding the working fluid between the low-pressure and
high-pressure sections includes a first deflector section, a first
channel, a second deflector section and a second channel, in that
order. The first deflector section deflects the working-fluid flow
outwardly away from the rotor. The first channel spreads the flow
out fanwise around and perpendicularly to the compressor axis. The
second deflector section deflects the flow back towards the shaft
and the second channel supplies the flow to the high-pressure
section entry perpendicularly to the compressor axis. At least one
of the two channels has at least one cooling element disposed
therein.
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:
The drawing illustrates a cross-sectional view of a multistage
compressor according to the invention.
Referring to the drawing, the multistage compressor has a rotor 1
on which six axial sets 2-7 of axial-flow blades are mounted in a
first section and three radial-flow rotors 8-10 in a second
section. Extending around rotor 1 is a casing 11 having an entry
channel 12 for the entry of fluid for compression. A channel 13 is
disposed at the opposite end for exiting of compressed fluid. The
axial-flow section of the compressor comprises a blade carrier 14
in which seven sets 15-21 of guide blades are mounted. Each
individual blade of the sets 15-21 has a root which is mounted in
the blade carrier and on which bent levers 24, engaging in circular
grooves 22 in adjustment cylinder 23, are disposed. A toothed rack
25 is positioned at the bottom of the cylinder 23 to enable the
cylinder 23 to be adjusted to suit operating requirements by means
of a pinion 26 of a motor 27.
In addition, the adjustable guide blades 15-21 which are adjustable
around a radial axis are followed by at least one axial-flow stage
having an adjustable exit guide blade 21 and a non-adjustable entry
guide blade for the channel 29.
Disposed between the last set 21 of axial-flow rotor blades and the
first radial-flow rotor 8 is a deflector part 28 which is connected
to the casing 11 and in which the axial flow from the first section
of the compressor is converted into an outwardly directed radial
flow. Following section 28 is a channel 29 which is directed
radially outwards and which acts as a diffusor and through which
the fluid flows to go through a second deflector section 30 into a
second channel 31. The second channel 31 extends radially inwards.
After further deflection, the flow enters the first radial flow
rotor 8. The inwardly directed channel 31 has cooling elements 32
which reduce the heat of compression acquired by the fluid in the
axial-flow section of the compressor. There is, therefore,
recooling of the fluid being compressed, and so a very high
compression ratio can be used as early as the first radial-flow
stage before any further cooling is given by elements 33. After
compression in the next rotor 9, the fluid is recooled by elements
34 before being compressed to its final pressure by rotor 10.
The cooling elements 32 together have a larger cooling area than do
the elements 33, 34, since the axial-flow section of the compressor
compresses the fluid to the maximum permissible temperature,
whereas in a radial-flow stage only the greatest pressure
difference, with a reduced temperature rise occurs.
The diffusor type radial-flow channel 29 can have appropriate guide
elements which can also be devised as cooling elements.
The invention thus provides a compressor which can be constructed
of relatively short lengths. Because of this, the rotor bearings
can be closely spaced with a resultant reduction of whirling. Also,
a number of radial-flow stages can be used as there is no axial
reversal of the working fluid flow.
* * * * *