US2717118A - Turbo-compressor - Google Patents

Description

Sept. 6, 1955 H. WALTER l TURBO-COMPRESSOR Filed March 7, 1952 2 Sheets-Sheet 1 FROM P\PE LINE I8 FIG. 2

H ELLMUTH WA LTER IN VEN TOR.

Sept. 6, 1955 H. WALTER 2,717,118

TURBO-COMPRESSOR Filed March 7, 1952 2 Sheets-Sheet 2 To REGENERATQR PIPE I INE Iooo 40 I9 psI 5 3l 4Z I IZ I3 30 Z445 G TO FROM 25 REGENER' HEATER A'roR Izoo 4 l5 45 Io I4 ,/Izoo psI psI ZZ |3 2| 28 Z7 26 32 800 psI FRO M PIPE LINE IN V EN TOR.

United States Patent O rURrsocoMPREssoR Hellmuth Walter, Upper Montclair, N. J., assignor to Worthington Corporation, acorporation of Delaware Application March 7, :19:52, Serial No. 4275,301

1.0 Claims. (Cl. ISO-M6) This invention relates to 'turbo-compressors land -more particularly to a ycombined turbine and compressor runit, particularly adapted for use in a gas -or vapor compressing unit `for compressing :flowing v.gas or vapor fin an :isolated system, wherein the energy required forrcotrnpression is delivered :from heating the gases iin one or more components of .the system; however, Vfhe'fuse lof the present turbo-compressor is no't limited tto such "para ticular use but may 'be employed wherever 'the 'use -of a turbo-compressor as set forth herein is deemed ladvantageous or practical.

An object of the present invention is tto provide la turbo-compressor 'wherein rthe entire 'turbine and compressor units are enclosed in a single casingor shell funder the inlet or outlet pressure of the gas or vapor thu's avoiding leakage, eliminating stuffing 'boxes and damage ot shafts at stutlng boxes or seals.

Another object `of 'the -present invention i's hto fprovide a turbo-compressor for a combined 'turbine Eand compressor unit which is relatively small -and Llight in 'weight with consequent low cost-of manufacture and installation and one wherein rotational problems are simplified 'and end thrust is compensated by regulation or routing fof the ow paths vof the gas or vapor through the turbine and compressor.

Another object of vthe present invention is to provide a turbo-compressor wherein the gas or vapor enters 'the unit in an axial direction and is distributed in a -concentric fashion which aiords an even distribution of temperature around the circumference of the unit -due to uneven expansion, and further to provide a turbo-compressor, wherein limited leakage of gas being compressed is utilized to cool the faces of the 'turbine wheel.

With these and other objects in view, as Amay appear from the accompanying specification, the invention 'consists lof various features of construction and combination of parts, which will be first described -in connection with the accompanying drawings, showing a turbo-compressor -of a preferred form embodying the "invention, and the features forming the invention will `be specifically pointed out inthe claims.

In the drawings:

Figure 1 is a side elevation of one form of the turbo compressor.

Figure 2 is a longitudinal section through vthe vtur-'bocompressor shown in 'Figure l.

Figure 3 is a side elevation of another form of 'the turbo-compressor, and

Figure 4 is a longitudinal section vthrough 'the fform of the turbo-compressor shown in Figure 3.

The turbo-compressor or combined turbine and Acornpressor unit is particularly applicable for use in -a icornpressing unit for compressing flowing gas or vapor in an isolated system such as shown-in myco-'pe'nding application, Serial No. 181,5"12, tiled August 25, 111950, wherein, due to pressure losses in the flowing gas or vapor caused by frictional tiiow, etc., it is desirable to raise the "pressure of the owing gases or vapor to their initial or entrance jpressure or to any desired pressure at spaced stations along the line of flow and in whichsystems the energy required for compression is derived from heating the gases in one or more components `of the compressing unit or system. In the following specication, for the purpose of clarification `of the descrip.; tion, the turbo-compressor could be described as used -in such a system as that above referred to, but it is to be understood that the turbo-compressor yof the present Ain-v vention is not to be limited to such particular use.

In the form of .the invention illustrated in Figures 1 and 2 of the drawings, the turbine and compressor units are enclosed in a casing 1 which `is 'made `up of three, parts, one substantially bell-shaped cover 2 for the outlet end of the compressor and two horizontally split halves 3 and 4 for enclosing the turbine, compressor proper and their connecting elements. In the form ofthe `irrvent-ion shown in Figures 3 and 4 of the drawings, the casing 5 consists of only two substantially barrel-shaped sections 6 and 7. The assembled turbine and compressor unit is inserted longitudinally into the section 7 from the end thereof which is closed by the cover section 6. The form of invention shown in Figures 3 and 4 of 'the drawings minimizes the number of casing joints t'o :be sealed against leakage, while the form of the invention shown in Figures l and 2 permits more ready accessi bility to the turbine and compressor units -for ,purposes of repairor replacement. In all other respects lthe two forms of the turbo-compressor are approximately the same, differing one from the other in detail features occasioned by the difference in the construction 'olf 'the casings.

The combined turbine and compressor unit includes a quill shaft 10 which is attached at one end thereof fby suitable bolts 11 or other attaching means to anfannular ring 12 which .is attached to the Shell .1 or 5 fby longitudinally spaced ribs 13 so that the quill shaft 510 is supported axially within the casing and yprovides the advantages of an over'hung shaft. "Suitable roller `or ball bearings 14 rotatably support the hollow hub fshaft .15 which carries the radiating peripheral blades 16 of the compressing unit. As shown in the drawings, the compressing unit is of the rotational type in 'contradistinction to the Vdirect-displacement reciprocating type of 'compressor, The rotatable blades 16 of the 'compressor cooperate with the stationary vanes 17 of the compressor unit 1 compressing `the gases or vapors 'the pressure of which is t'o be raised. The inlet of the gas `or vapor.

the pressure of which is to be raised, is intermediate the :ends/of fthe casing of the turbo-compressor 'asrshown at 18 Vand it opens into 'an annular passage 19 at A:the suction end of `t`he compressor. The 'fluid or gas 'to be compressed Iowsthrough 'the compressor proper'where its pressure lis raised and discharges through the annular converging passageway 20 into the 'axial 'outlet 2-1 at one end of the casing, i. e., at the outlet rendot the cover section 16. A streamline or projectile pointshapedfguide 2v2 has its base end `attached-in any suitable manner yto the -ring 12 `and :it projects into the cover f2 or 6 to form a continuation of the annular discharge passage gradually Yterminating .into fthe axial outlet :21.

A turbine 4wheel 23 is attached to the end of the rotating hub shaft 15 opposite the end of the shaft which .is attached to the supporting ring 1-2. While the turbine wheel 23 may be attached in any suitable manner t0 the hollow hub shaft 15, as shown in lFigures 2 and 4 of thev drawings, Ithe hollow hub shaft 1`5 is shown as 'having its end opposite the end which is attached to the supporting ring I12 closed 'by disc 24 which 'may `be 'formed as a 'pa'rt 'of the shaft S15 or welded thereto 'as-desired. The hub of the turbine wheel Y2:3 is attached in any 'suitable manner preferably bybolting as shown at 25ftoft`he "closed end of the rotating hub shaft so that rotation of the turbine wheel will rotate the compressor rotor. The blades 26 of the turbine wheel 23 cooperate with the stationary vanes 27 as is usual in a turbine construction and the motive uid or gas for driving the turbine wheel enters the casing 1 or 5 axially through the inlet 28 at the end opposite to the outlet 21. The incoming motive gas is directed into the annular inlet passage 29 by streamline or projectile shaped guide element 30 which is stationarily attached to the shell or casing 1 or 5 in any suitable manner such as by the annularly spaced ribs 31. The annular discharge or outlet passage 32 of the turbine structure opens out through an outlet opening 33 extending radially of the casing and at the opposite side of the axis of the turbo-compressor from the inlet 18 for the gases to be compressed.

The two forms of the invention shown in Figures 2 and 4 are identical in all of the features just above described but differ as previously stated in specific details' as follows: p

In the construction of the turbo-compressor shown in Figure 2 of the drawings the annular discharge passage 32 of the turbine and the annular inlet passage 19 of the compressor are separated by a web 34 which is formed integrally with the sections 3 and 4 of the casing 1. Suitable sealing means indicated at 35 are carried by the ring-like laterally extending wings of the partition 34 and form a seal between the partition and the rotary hub shaft 15.

The rotary hub shaft 15 is provided with a plurality of small radiating openings or passageways 36 formed therein which open into the space within the hollow rotary hub shaft 15 and outwardly of the quill shaft 10 and the closed end 24 is also provided with a plurality of small openings or passages 37 which communicate with the space within the hollow shaft and open out against the inner side of the turbine wheel 23 thus a small amount of the gas being compressed and any gas that leaks past the first of the seals 35 ows through the passages or openings 37 against the turbine wheel 23 for cooling the turbine wheel. As shown in Figure 2 of the drawings the openings or passages 36 open into the compressing chamber of the compressor at an intermediate stage of com# pression preferably near to the initial or Suction compression stage.

In Figure 4 of the drawings wherein the section 7 of the casing 5 is formed of a single casting the annular turbine discharge passage 32 is separated from the annular inlet passage of the gas to be compressed by a spacer ring 40 which is attached to the casing section 7 in any suitable manner as shown at 41. Suitable seals 42 are placed between the inner circumference of the ring 40 and the rotary hub shaft 15. The ring 40 is shown as hollow having an annular chamber 43 therein which will collect any leakage from either the turbine discharge or the compressor inlet. Any leakage gas collecting in the annular chamber 43 passes through suitable small openings or passages 44 into the space 45 within the hollow hub shaft 15 and about the quill shaft 10. The closed end 24 of the rotary hollow hub shaft 15 is provided with a plurality of small passages or openings 45 extending therethrough through which the leakage gas passes against the inner surface of the turbine wheel 23 for cooling the turbine wheel. If additional cooling is provided for cooling the turbine wheel and for cooling the bearings 14 small passages or openings 46 may be made in the rotary hollow hub shaft 15 opening into an intermediate stage of compression in the compressing chamber and into the annular space 45 for augmenting the leakage from the chamber 43.

It will be understood that the invention is not to be limited to the specific construction or arrangement of parts shown, but that they may be widely modified within the linvention dened by the claims.

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What is claimed is:

1. In a turbo-compressor, a casing, a turbine in said casing, an axial compressor in said casing, an annular supporting ring in said casing, a quill shaft attached to said ring and extending axially in the casing, a hollow hub shaft rotatably mounted on said quill shaft and having one end closed, said turbine including a rotor, said turbine rotor attached to the closed end of said hub shaft, said compressor including rotary blades, said blades attached to said hollow hub shaft for rotation therewith.

2. A turbo-compressor as claimed in claim l wherein said hub shaft is spaced from said quill shaft to form a cooling space within the hub shaft, said hub shaft being provided with openings opening therethrough into the compression space of the compressor to admit gas from the compressor into said cooling space.

3. A turbo-compressor as claimed in claim 1 wherein said hub shaft is spaced from said quill shaft to form a cooling space within the hub shaft, said hub shaft being provided with openings opening therethrough into the compression space of the compressor to admit gas from the compressor into said cooling space, said turbine rotor and the closed end of said hub shaft provided with openings opening into said cooling chamber to permit gas from the chamber to cool the turbine rotor.

4. A turbo-compressor as claimed in claim 1 wherein said hub shaft is spaced from said quill shaft to form a cooling space within the hub shaft, said hub shaft being provided with openings opening therethrough into the compression space of the compressor to admit gas from the compressor into said cooling space, said turbine rotor and the closed end of said hub shaft provided with openings opening into said cooling chamber to permit gas from the chamber to cool the turbine rotor, a hollow annular spacer ring in said housing, said hub shaft having radial openings therein opening into the space within said annular spacerring and said cooling chamber.

5. In a turbo-compressor, a turbine, an axial compressor, a substantially barrel-shaped casing including the turbine and compressor enclosing part having one end portion gradually decreasing in cross-sectional area to its outer end to form an axial inlet for gas under pressure to the turbine, said casing including a cover attached to one end of the turbine and compressor enclosing part remote from its axial inlet, said cover gradually decreasing in cross-sectional area to its outer end to form an axial outlet for gas compressed by said compressor, an annular spacer ring in said casing between the outlet for expanded gas and the inlet for gas to be compressed, said spacer ring having a leakage receiving chamber therein for collecting leakage from either the turbine discharge or the compressor inlet.

6. In a turbo-compressor, a substantially barrel-shaped casing, a combined turbine and axial ow compressor unit mounted in said casing, said casing decreasing in crosssectional area at its ends and having an axial inlet at one end thereof for high pressure gas flowing to the turbine and an axial outlet at the other end of the casing for high pressure gas discharged by the compressor, said inlet and outlet being in axial alignment, said casing having a radial outlet for expanded gas from the turbine and a radial inlet for gas to be compressed disposed in substantially opposed relation on the casing, an annular ring in said casing outwardly of the discharge end of said axial compressor, a hollow quill shaft attached to said supporting ring and enclosed wholly within the casing, a hollow hub shaft rotatably supported by said quill shaft in spaced relation thereto to provide a cooling chamber within the hub shaft opening into said hollow quill shaft, said hub shaft provided with radial openings having communication with the compression space of the compressor to admit gas from the compressor into said cooling space.

7. A turbo-compressor as claimed in claim 6 including an annular spacer ring in said casing between the outlet for expanded gas and the inlet for gas to be compressed,

said spacer ring having a leakage receiving chamber therein for collecting leakage from either the turbine discharge or the compressor inlet.

8. In a turbo-compressor, a substantially cylindrical casing, a combined turbine and axial flow compressor unit rotatably mounted in said casing, said casing decreasing in cross-sectional area at its ends and having an axial inlet at one end thereof for high pressure gas owing to the turbine and an axial outlet at the other end of the casing for high pressure gas discharged by the compressor, said casing having a radial outlet for expanded gas from the turbine and a radial inlet for gas to be compressed, said casing having annular passages therein for the iiow of gas to and from the turbine and the ow of gas to and from the compressing unit whereby gases are distributed in a concentric passage within the shell to afford even distribution of temperature around the circumference of the shell, an annular ring in said casing outwardly of the discharge end of said axial compressor, a quill shaft attached to said suporting ring and enclosed Wholly within said casing, a hub shaft rotatably supported by said quill shaft in spaced relation thereto, a plurality of attaching ribs connecting said annular ring to said casing, said rings extending radially across the annular passage for the ow of gas from the compressor, said turbine and compressor each comprising a rotor, said rotors being carried by said hub shaft.

9. A turbo-compressor as claimed in claim 8 including an annular spacer ring in said casing between the outlet for expanded gas and inlet for gas to be compressed, said spacer ring having a leakage receiving chamber therein for collecting leakage from either the turbine discharge or the compressor inlet.

10. In a turbo-compressor, a turbine, an axial compressor, a substantially barrel-shaped casing including the 1 turbine and compressor enclosing part having one end portion gradually decreasing in cross-sectional area to its l il outer end to form an axial inlet for gas under pressure to the turbine, said casing including a cover attached to one end of the turbine and compressor enclosing part remote from its axial inlet, said cover gradually decreasing in cross-sectional area to its outer end to form an axialvoutlet for gas compressed by said compressor, said turbine and compressor enclosing part of said casing having an annular passage therein for the ow of gas to and from the turbine and the ow of gas to and from the compressor, streamlined guides carried in said areas of decreasing cross-sectional area to provide gradual merging of the axial inlet and axial outlet into respective annular passages communicating therewith, an annular ring in said cover adjacent to its point of connection with the turbine and compressor enclosing part, a hollow quill shaft attached to said supporting ring, a hollow hub shaft rotatably supported by said quill shaft in spaced relation thereto to provide a cooling chamber within the hub shaft opening into said hollow quill shaft, said hub shaft provided with radial openings having communication with the compression space of the compressor into said cooling space.

References Cited in the tile of this patent UNITED STATES PATENTS 2,173,595 Shutte Sept. 19, 1939 2,322,824 Buchi June 29, 1943 2,356,557` Anxionnax et al Aug. 22, 1944 2,364,189 Buchi Dec. 5, 1944 2,429,681 Griffith Oct. 28, 1947 2,480,095 Buchi Aug. 23, 1949 2,577,179 Buchi Dec. 4, 1951 2,579,049 Price Dec. 18, 1951 2,599,470 Meyer June 3, 1952 2,647,366 McCann Aug. 4, 1953

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