U.S. patent number 3,892,499 [Application Number 05/378,428] was granted by the patent office on 1975-07-01 for multistage turbocompressor having an intermediate cooler.
This patent grant is currently assigned to Sulzer Brothers Ltd.. Invention is credited to Rene Strub.
United States Patent |
3,892,499 |
Strub |
July 1, 1975 |
Multistage turbocompressor having an intermediate cooler
Abstract
The compressor housing is connected to the cooler by a casing
duct to direct the intially compressed gas to the cooler while a
central duct within the casing duct returns the cooled air to the
housing and to the second compressor. The heated wall of the
central duct serves to vaporize any droplets of fluid in the return
gas flow which might otherwise damage the second compressor.
Inventors: |
Strub; Rene (Winterthur,
CH) |
Assignee: |
Sulzer Brothers Ltd.
(Winterthur, CH)
|
Family
ID: |
4364058 |
Appl.
No.: |
05/378,428 |
Filed: |
July 12, 1973 |
Foreign Application Priority Data
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Jul 13, 1972 [CH] |
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10517/72 |
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Current U.S.
Class: |
415/179; 415/143;
415/169.2; 417/372 |
Current CPC
Class: |
F04D
29/5826 (20130101); F04D 17/025 (20130101) |
Current International
Class: |
F04D
29/58 (20060101); F04D 17/02 (20060101); F04D
17/00 (20060101); F01d 005/08 () |
Field of
Search: |
;417/372
;415/179,168 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Husar; C. J.
Attorney, Agent or Firm: Kenyon & Kenyon Reilly Carr
& Chapin
Claims
I claim:
1. In a multistage turbocompressor having a compressor housing
including an inlet and an outlet and an intermediate cooler outside
said housing;
a casing duct connected between said housing and said cooler
downstream of said inlet for passing a flow of heated compressed
gas from said housing to said cooler for cooling therein, and
a central duct enclosed within said casing duct and connected
between said cooler and said housing upstream of said outlet for
passing the flow of cooled compressed gas from said cooler to said
housing for passage out of said outlet.
2. In a multistage turbocompressor as set forth in claim 1, said
casing duct and said central duct each having a bend therein.
3. In a multistage turbocompressor as set forth in claim 1, said
housing being split in two halves in an axial plane and said ducts
being connected to the lower half of said housing.
4. In a multistage turbocompressor as set forth in claim 3, wherein
two said casing ducts are connected to said lower housing half
symmetrically of a vertical axial plane of said housing.
5. In a multistage turbocompressor as set forth in claim 1, means
connected between said casing duct and said central duct for
selectively introducing a variable amount of heated gas from said
casing duct into the flow of cooled gas in said central duct.
6. A multistage turbocompressor comprising a housing including an
inlet and an outlet;
a first compressor in said housing downstream of said inlet for
heating and compressing a flow of gas to a first pressure;
a second compressor in said housing downstream of said first
compressor and upstream of said outlet for compressing the flow of
gas to a higher pressure than said first pressure;
a cooler outside said housing for cooling the flow of heated
gas;
a casing duct connected between said housing and said cooler for
passing the flow of heated gas to said cooler from said first
compressor; and
a central duct enclosed within said casing duct and connected
between said cooler and said housing for passing the flow of cooled
gas from said cooler to said second compressor.
7. A multistage turbocompressor as set forth in claim 6 wherein
each duct has a bend therein for deflecting a respective flow of
gas therein.
8. A multistage turbocompressor as set forth in claim 6 wherein
said each compressor is an axial flow compressor.
9. A multistage turbocompressor as set forth in claim 6 wherein
said first compressor is an axial flow compressor and said second
compressor is a radial flow compressor.
10. A multistage turbocompressor as set forth in claim 6 further
comprising a means connected between said casing duct and said
central duct for selectively introducing a variable amount of
heated gas from said casing duct into the flow of cooled gas in
said central duct.
11. A multistage turbocompressor comprising
a compressor housing having an inlet and an outlet,
a first plurality of compressor stages in said housing adjacent and
downstream of said inlet to receive and compress a flow of gas to a
first pressure,
a cooler outside said housing for cooling the flow of compressed
gas,
a casing duct connected between said housing and said cooler for
passing the flow of compressed gas to said cooler,
a central duct concentric to said casing duct and connected between
said cooler and said housing for passing the flow of cooled gas
from said cooler to said housing downstream of said compressor
stages, and
a second plurality of compressor stages in said housing downstream
of said first compressor stages and upstream of said outlet for
compressing the flow of gas from said cooler and central duct.
Description
This invention relates to a multistage turbocompressor having an
intermediate cooler.
Heretofore, multistage turbocompressors have been known to use an
intermediate cooler between various compressors in order to cool a
gaseous working medium, e.g. steam, flowing between the
compressors. However, a danger has existed that the gaseous working
medium may cool to such an extent, either temporarily or for a
relatively long time, as to allow the water vapor therein to begin
to condense. Should this occur, the condensed water vapor would be
delivered as water droplets to the blading channels of the
turbocompressor and would cause damage through erosion and
depositing of impurities contained in the gas flow. Axial blading
is particularly endangered because higher speeds of the working
medium to be compressed are generated relative to the blade
surfaces driving the medium than is the case with the blading of a
radial compressor.
Accordingly, it is an object of the invention to prevent the
introduction of drops of condensate in a gaseous working medium
into the blading of a compressor.
It is another object of the invention to provide a simple
construction for removing drops of condensate from a flow of
compressed gas leading to a turbocompressor from an intermediate
cooler.
Briefly, the invention provides a multistage turbocompressor
comprised of a compressor housing and an intermediate cooler
outside the housing with a casing duct between the housing and
cooler and a central duct enclosed within the casing duct and
between the cooler and housing. The casing duct is connected to
pass a flow of heated compressed gas from the housing, for example,
from an initial compressor therein, to the cooler for cooling to
suitable temperature for subsequent use. The central duct is
connected to pass the flow of cooled compressed gas back to the
housing, for example, to a second compressor. During passage
through the casing duct, the heated gas heats the wall of the
central duct. The resultant heat in the wall of the central duct
then heats any condensate in the counter-current flow of cooled gas
within the central duct to vaporize the condensate. As a result,
the return flow of gas becomes free of condensate.
Gas turbine equipment such as described in Swiss Pat. Nos. 214,837
and 221,377 have been known to use piping systems with a central
duct disposed within a casing duct. However, these piping systems
have been used to conduct a high-temperature gas through the
central duct. In order to lower the temperature of a tube wall
stressed by the pressure of the gas, a cooler gas has been
conducted in the outer casing duct. In this way, it has been
possible to obtain thermal relief of the wall loaded by the high
internal pressure, avoiding strength problems and leak-proofing
difficulties. In accordance with the invention, the hot gas is
conducted in the outer casing duct and the cool gas in the central
duct. Thus, the tube wall dividing the casing duct from the central
duct can be maintained at a high-temperature by means of the flow
of not-yet-cooled gas. As a result, the flow of cool gas laden with
drops of condensate is surrounded on all sides by a
high-temperature wall. Upon encountering this wall, because of the
increase of surface area, the drops become vaporized before
reaching the blading of the compressor.
The compressor may have an axial stage upstream of the exit point
to the cooler of the medium being compressed, and may have a radial
stage following the reentry of the cooler medium. The invention is
of special importance for compressors with use axial stages
following the re-entry of the cooled medium.
The function of the casing duct can be substantially facilitated by
forming a bend in the casing duct as well as in the central duct
since the drops of condensate will impact against the wall, and
produce a greater surface area of contact. Thus revaporization can
be accelerated.
The casing duct and central duct can advantageously be connected to
the lower half of the housing where the housing is split in two
halves. Also, it is possible to have two casing ducts disposed
symmetrically of the perpendicular axial plane of the turborotor
with each connected to the housing. Finally, a means may be
disposed between the casing duct and the central duct to
selectively introduce a variable amount of heated gas from the
casing duct into the flow of cooled gas in the central duct in
order to further promote the vaporization of the condensate
drops.
These and other objects and advantages of the invention will become
more apparent from the following detailed description taken in
conjunction with the accompanying drawing in which:
FIG. 1 illustrates an axial cross-sectional view of a
turbocompressor according to the invention;
FIG. 2 illustrates a cross-sectional view taken on the plane II--II
of FIG. 1.
FIG. 3 illustrates an axial cross-sectional view of a further
turbocompressor construction according to the invention made as a
purely axial compressor; and
FIG. 4 illustrates a cross-sectional view through a compressor with
separate intermediate coolers disposed at both sides according to
the invention.
Referring to FIGS. 1 and 2, an axial-radial turbocompressor
includes in a housing 1 in which a rotor 2 is mounted and which has
an inlet A for receiving air or a gas. The rotor 2 carries axial
rotor rings 3 to 10 to compress air or a gas to a pressure at which
the temperature rises to such an extent that intermediate cooling
is necessary. The rotor 2 also carries radial stages 11 and 12 of a
radial compressor to compress the gas further to a final pressure
after cooling. The housing 1 also has an outlet B at the end of the
radial compressor for the exhaust of the compressed gas.
In order to intermediately cool the gas, a casing duct 13 is
connected to the housing 1 between the axial stages 3 to 10 and the
radial stages 11, 12 (FIG. 1) and extends to a cooler 14 (FIG. 2)
to conduct the flow of heated compressed gas to the cooler 14. In
addition, a central duct 15 is enclosed within the casing duct 13
and extends from the cooler 14 to the housing 1 to conduct the flow
of cooled compressed gas back to the housing and to the radial
stages 11, 12. As shown, both ducts 13, 15 have a curved or bent
position to deflect the respective flows of gas for purposes as
described below.
Depending on the kind of gas to be compressed, the condition of the
gas before reaching the compressor, and the condition desired at
emergence from the compressor, the gas may be cooled in the
intermediate cooler 14 to such an extent that the water contained
in the gas before compression (or some other condensable inclusion)
becomes condensed into drops. These drops are carried along by the
gas flowing back into the compressor, and would, without an
introduction of heat, only revaporize during the compression in the
radial stage 11, and deposit non-vaporized impurities on the blade
surfaces. Non-vaporized residues might even arrive in stage 12. As
a result, and because of the high speeds at which the drops strike
the rotor parts or other compressor parts, erosion and premature
wear of these parts may occur.
By running the central duct 15 inside the casing duct 13, the wall
of the central duct 15 is supplied with heat from the gas heated
through compression in stages 3 to 10 and flowing into the casing
duct 13. As a result, the drops of liquid carried along by the
cooled gas receive so much heat that they revaporize and, as vapor,
can no longer cause damage to the radial rotors 11 and 12. The
solid constituents are now dry, and are forced through the
compressor without becoming deposited on the blades.
The vaporization of the drops of liquid in the central duct 15 can
occur, in part, in the suspended state through the radiation of
heat from the wall and also, in part, through contact with the duct
wall. Because of the turbulence of the gas and the curved portions
of the duct 15 some of the drops strike the heated duct wall and
thereby become broken up. This gives the drops an enlarged surface
area, thereby promoting more rapid vaporization. If there is a
danger of a particularly great formation of liquid drops, then it
is possible to install guide elements in the central duct to
separate the drops out of the gas flow and conduct the drops
against the wall. Such guide elements could also aid in the
vaporization of the drops of condensate if heated to a sufficient
temperature by radiation from the duct walls.
Referring to FIG. 3, wherein like reference characters indicate
like parts as above, an axial compressor having axial stages 16 to
21 follow the intermediate cooler (not shown). Axial stages are
more endangered by drops in the gaseous working medium being
compressed and by deposits than are radial stages, and in their
flow, undergo greater deviations than radial compressors.
Naturally, the most endangered parts are the blades of the
introduction-stator 22 first reached by the intermediately cooled
gas. These blades do not receive the flow of gas from the central
duct 15 as uniformly as do the blades of the following rotors 16 to
21 and stators 23 to 28.
Finally, referring to FIG. 4 wherein like reference characters
indicate like parts as above, aa turbocompressor can be provided at
each side of the housing 1 with an intermediate cooler 14. The
housing 1 is split into two halves, with the connection of each
cooler 14 made in the lower housing half 29 by flanges 30. This
facilitates access to the rotor 2 for maintenance and overhauling
work.
A means 31-33 is also provided between the casing duct 13 and the
central duct 15 in order to selectively introduce a small variable
amount of not-yet-cooled medium being compressed from the casing
duct 13 into the central duct 15. This means includes a pipe 31
connecting the casing duct 13 to the central duct 15, a series of
outlets 32 in the pipe 31 to introduce the heated gas into the
central duct 15 and a valve 33 for controlling the amount of flow
through the pipe 31. This conducts so much heat to the cool gas in
the central duct 15, which still contains drops, that any drops not
reaching the wall and not sufficiently heat-irradiated by the wall
become vaporized. An undesirable reheating of the cooled gas is not
to be expected because the brought-in heat is used chiefly to
vaporize the drops.
* * * * *