US2925954A - Compressor group with intercooler - Google Patents

Compressor group with intercooler Download PDF

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Publication number
US2925954A
US2925954A US646461A US64646157A US2925954A US 2925954 A US2925954 A US 2925954A US 646461 A US646461 A US 646461A US 64646157 A US64646157 A US 64646157A US 2925954 A US2925954 A US 2925954A
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compressor
annular
cooler
inlet
flow
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US646461A
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Spillmann Werner
Oechslin Konrad
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Sulzer Escher Wyss AG
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Escher Wyss AG
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/58—Cooling; Heating; Diminishing heat transfer
    • F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps
    • F04D29/5826—Cooling at least part of the working fluid in a heat exchanger
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D19/00—Axial-flow pumps
    • F04D19/02—Multi-stage pumps

Definitions

  • the invention relates to a compressor group, in particular of a gas turbine plant comprising two intercoupled axial-flow compressors traversed by the flow medium in series in the same direction and a cooler interposed in the flow path between the two compressors.
  • annular cooler In a known compressor group of this type, an annular cooler is arranged coaxially with the machine axis, an annular diffuser at the outlet of the first compressor conveying the flow medium leaving the first compressor to the cooler inlet and the flow medium leaving the cooler arriving in an annular inlet chamber of the second compressor.
  • the annular cooler encircles the outlet chamber of the first compressor as well as the inlet chamber of the second compressor. This does not only require a relatively large diameter for the annular cooler with a correspondingly large requirement in space, but, further, the flow medium leaving the first compressor must, before being introduced to the cooler, be returned through about 180 in a direction opposite to the direction of flow in the compressors, and thereafter, still before reaching the cooler, the flow direction must be changed again. The same applies to the flow medium leaving the cooler before entering the following compressor.
  • a flow reversal of 180 has proved disadvantageous in a diffuser with respect to its efliciency.
  • large flow losses occur in the annular diffuser following the first compressor of the arrangement described above.
  • the disadvantage referred to is avoided by the invention in that the annular diffuser is formed as an annular chamber diverging regularly with respect to the compressor axis, at least part of the annular inlet chamber of the second compressor being encircled by said annular diffuser, and in that the inlet end of the cooler when viewed from the first compressor is situated beyond the inlet of the second compressor.
  • the drawing illustrates by way of example an embodiment of the invention.
  • the compressor group of a gas turbine plant comprises two inter-coupled axial flow compressors having bladed rotors 1 and 2 traversed in series by the working medium, and an annular cooler 3 which is coaxial with the machine axis.
  • the inlet of the second compressor is situated axially adjacent the outlet of the first compressor.
  • the two compressors are driven by a turbine having a bladed rotor 4.
  • the cooler 3 is arranged in the flow path between the outlet of the first compressor and the inlet of the second compressor. It is located in a common housing 6 with the rotors of the compressors and the turbine, the housing being split at 5.
  • the compressor 2 is disposed between the first compressor and the turbine.
  • the compressors and the tur- United States Patent 2,925,954 Patented Feb. 33, 1960 bine are all traversed by the working medium axially in the same direction, namely in the direction from the first compressor toward the turbine.
  • the rotor 2 of the second compressor is encircled by a stationary blade carrying shell 2
  • the annular intercooler 3 encircles the shell 2 and the rotor 2.
  • annular diffuser 7 in the form of an annular chamber diverging regularly with respect to the compressor axis and mainly bounded from outside by a conical part of the housing 6 and from inside by a conical annular partition wall 6
  • the annular dilfuser conveys the working medium leaving the first compressor to the inlet end of the cooler 3.
  • the latter is traversed by the working medium in a direction axially opposite to the direction of flow in the compressors 1 and 2.
  • the connection between the outlet end of the annular diffuser 7 and the inlet end of the cooler 3 is formed by an annular channel 8 encircling the cooler 3, and an inlet chamber 8 both bounded from outside by a part of the housing 6.
  • This inlet chamber is defined partly by the partition wall 6 and by a further partition wall 6 situated within the housing 6.
  • the rotors 4 and 2 for the turbine and the second compressor are made in one piece.
  • the rotor 1 for the first compressor is flange coupled to a terminal shaft portion of this one piece. All three rotors are supported at a total of only three points, in bearings 10, 11, 12-at the two outer ends and between the two compressors.
  • the turbine rotor 4 is enclosed by an inner housing 4 Y which also defines an inlet chamber 4 for the working medium flowing to the turbine.
  • the housing 6 encircles the annular inlet chamber 8 for the working medium flowing to the cooler 3 and also encloses the inner turbine housing, whereby a discharge space 9 for the working medium leaving the second compressor is left between the two, and a discharge chamber 4 for the working medium leaving the turbine.
  • An interior partition wall 6 separates the discharge space 9 from the annular chamber 8
  • the flow medium is only gently deflected in the annular diffuser 7 after leaving the impellers of the first compressor.
  • the diffuser has a relatively long path in which the direction of the flow medium is hardly changed at all. Thus the amount of recovered kinetic energy from the flow medium leaving the first compressor, is high. More severe deflections occur only at points where the speed of the flow medium is considerably reduced, so that the losses caused thereby are negligible.
  • the housing 6 has a comparatively small outer diameter which enhances the strength. The construction described is therefore a suitable set of machines for gas turbine plants having a pressurized working medium circuit.
  • a compressor group comprising two coaxial and inadjacent to but distinct from the outlet of the first compressor, said second compressor having also an outlet at the end remote from its inlet; an intercooler generally cylindrical in external contour, mounted coaxially with said compressors and encircling the second thereof, said intercooler having an annular inlet communicating directly with the annular outlet of the first compressor, and an outlet chamber communicating with the annular inlet of the second compressor, said intercooler including a. double-walled enclosing envelope serving as a difiuser and comprising two conical walls between which the annular outlet of the first compressor discharges compressed medium, said two walls flaring at dilferent respective angles from the compressor axis so as to be in convergaoamae;
  • said conical walls extending to and merging with spaced coaxial cylindrical walls which are portions of said envelope, the spacing of the cylindrical envelope walls approximating the closest approach of the conical walls toward each other.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Description

Feb. 23, 1960 W. SPILLMANN ET AL COMPRESSOR GROUP WITH INTERCOOLER I Filed March 15, 1957 m 01 f P Q I INVENTOR.
. warn erspillmann n ii'onzud Oech sZz'n ATTORNEIJ COMPRESSOR GROUP WITH INTERCOOLER Werner Spillmann, Kilchberg, and Konrad Oechslin,
Zurich, Switzerland, assignors to Escher Wyss Aktiengesellschaft, Zurich, Switzerland, a corporation of Switzerland Application March 15, 1957, Serial No. 646,461 Claims priority, application Switzerland March 29, 1956 1 Claim. (Cl. 230-209) The invention relates to a compressor group, in particular of a gas turbine plant comprising two intercoupled axial-flow compressors traversed by the flow medium in series in the same direction and a cooler interposed in the flow path between the two compressors.
In a known compressor group of this type, an annular cooler is arranged coaxially with the machine axis, an annular diffuser at the outlet of the first compressor conveying the flow medium leaving the first compressor to the cooler inlet and the flow medium leaving the cooler arriving in an annular inlet chamber of the second compressor. In this known construction, the annular cooler encircles the outlet chamber of the first compressor as well as the inlet chamber of the second compressor. This does not only require a relatively large diameter for the annular cooler with a correspondingly large requirement in space, but, further, the flow medium leaving the first compressor must, before being introduced to the cooler, be returned through about 180 in a direction opposite to the direction of flow in the compressors, and thereafter, still before reaching the cooler, the flow direction must be changed again. The same applies to the flow medium leaving the cooler before entering the following compressor.
A flow reversal of 180 has proved disadvantageous in a diffuser with respect to its efliciency. Thus, large flow losses occur in the annular diffuser following the first compressor of the arrangement described above.
In a compressor group of the type hereinbefore specified, having an annular intercooler coaxial with the machine axis, in which an annular difluser at the outlet of the first compressor supplies the flow medium leaving the first compressor to the inlet of the cooler, the working medium leaving the cooler reaching an annular inlet chamber of the second compressor, the disadvantage referred to is avoided by the invention in that the annular diffuser is formed as an annular chamber diverging regularly with respect to the compressor axis, at least part of the annular inlet chamber of the second compressor being encircled by said annular diffuser, and in that the inlet end of the cooler when viewed from the first compressor is situated beyond the inlet of the second compressor.
The drawing illustrates by way of example an embodiment of the invention. The compressor group of a gas turbine plant comprises two inter-coupled axial flow compressors having bladed rotors 1 and 2 traversed in series by the working medium, and an annular cooler 3 which is coaxial with the machine axis. The inlet of the second compressor is situated axially adjacent the outlet of the first compressor. The two compressors are driven by a turbine having a bladed rotor 4. The cooler 3 is arranged in the flow path between the outlet of the first compressor and the inlet of the second compressor. It is located in a common housing 6 with the rotors of the compressors and the turbine, the housing being split at 5. The compressor 2 is disposed between the first compressor and the turbine. The compressors and the tur- United States Patent 2,925,954 Patented Feb. 33, 1960 bine are all traversed by the working medium axially in the same direction, namely in the direction from the first compressor toward the turbine. The rotor 2 of the second compressor is encircled by a stationary blade carrying shell 2 The annular intercooler 3 encircles the shell 2 and the rotor 2.
At the outlet end of the first compressor there is provided an annular diffuser 7 in the form of an annular chamber diverging regularly with respect to the compressor axis and mainly bounded from outside by a conical part of the housing 6 and from inside by a conical annular partition wall 6 The annular dilfuser conveys the working medium leaving the first compressor to the inlet end of the cooler 3. The latter is traversed by the working medium in a direction axially opposite to the direction of flow in the compressors 1 and 2. The connection between the outlet end of the annular diffuser 7 and the inlet end of the cooler 3 is formed by an annular channel 8 encircling the cooler 3, and an inlet chamber 8 both bounded from outside by a part of the housing 6. The inlet end of the cooler 3, as viewed from the first compressor, is situated beyond the inlet of the second compressor. At the outlet end of the cooler 3 there is located an annular chamber 9 encircled by the difiuser 7 and serving as an inlet chamber for the compressor 2. This inlet chamber is defined partly by the partition wall 6 and by a further partition wall 6 situated within the housing 6.
In the embodiment as illustrated, the rotors 4 and 2 for the turbine and the second compressor are made in one piece. The rotor 1 for the first compressor is flange coupled to a terminal shaft portion of this one piece. All three rotors are supported at a total of only three points, in bearings 10, 11, 12-at the two outer ends and between the two compressors.
The turbine rotor 4 is enclosed by an inner housing 4 Y which also defines an inlet chamber 4 for the working medium flowing to the turbine. The housing 6 encircles the annular inlet chamber 8 for the working medium flowing to the cooler 3 and also encloses the inner turbine housing, whereby a discharge space 9 for the working medium leaving the second compressor is left between the two, and a discharge chamber 4 for the working medium leaving the turbine. An interior partition wall 6 separates the discharge space 9 from the annular chamber 8 In the construction described, the flow medium is only gently deflected in the annular diffuser 7 after leaving the impellers of the first compressor. The diffuser has a relatively long path in which the direction of the flow medium is hardly changed at all. Thus the amount of recovered kinetic energy from the flow medium leaving the first compressor, is high. More severe deflections occur only at points where the speed of the flow medium is considerably reduced, so that the losses caused thereby are negligible.
Since, in constrast with known constructions, no direction-changing of the Working medium need take place radially within the annular cooler 3, the latter can have a smaller diameter. This also results in space saving and a saving in constructional expenses. The housing 6 has a comparatively small outer diameter which enhances the strength. The construction described is therefore a suitable set of machines for gas turbine plants having a pressurized working medium circuit.
What is claimed is:
A compressor group comprising two coaxial and inadjacent to but distinct from the outlet of the first compressor, said second compressor having also an outlet at the end remote from its inlet; an intercooler generally cylindrical in external contour, mounted coaxially with said compressors and encircling the second thereof, said intercooler having an annular inlet communicating directly with the annular outlet of the first compressor, and an outlet chamber communicating with the annular inlet of the second compressor, said intercooler including a. double-walled enclosing envelope serving as a difiuser and comprising two conical walls between which the annular outlet of the first compressor discharges compressed medium, said two walls flaring at dilferent respective angles from the compressor axis so as to be in convergaoamae;
ing relation with each other in the direction of medium flow between them, said conical walls extending to and merging with spaced coaxial cylindrical walls which are portions of said envelope, the spacing of the cylindrical envelope walls approximating the closest approach of the conical walls toward each other.
References Cited in the file of this patent UNITED STATES PATENTS 2,396,484 Allen et al. Mar. 12, 1946 I FOREIGN PATENTS 215,474 Switzerland on. 1, 1941
US646461A 1956-03-29 1957-03-15 Compressor group with intercooler Expired - Lifetime US2925954A (en)

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Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1120817B (en) * 1960-06-17 1961-12-28 Escher Wyss Ag Pre- or intermediate cooler of a gas turbine plant
US3056539A (en) * 1958-02-03 1962-10-02 Pullin Cyril George Gas turbine compressor units
US3209536A (en) * 1960-04-04 1965-10-05 Ford Motor Co Re-expansion type gas turbine engine with intercooler fan driven by the low pressure turbine
US3211362A (en) * 1963-04-05 1965-10-12 Int Harvester Co Turbochargers
US3795458A (en) * 1971-01-20 1974-03-05 Bbc Sulzer Turbomaschinen Multistage compressor
US3892499A (en) * 1972-07-13 1975-07-01 Sulzer Ag Multistage turbocompressor having an intermediate cooler
JPS5286707U (en) * 1975-12-24 1977-06-28
US4125345A (en) * 1974-09-20 1978-11-14 Hitachi, Ltd. Turbo-fluid device
US4431371A (en) * 1982-06-14 1984-02-14 Rockwell International Corporation Gas turbine with blade temperature control
US20040055740A1 (en) * 2002-09-20 2004-03-25 Meshenky Steven P. Internally mounted radial flow intercooler for a combustion air charger
US20040062644A1 (en) * 2002-09-27 2004-04-01 Meshenky Steven P. Internally mounted radial flow intercooler for a rotary compressor machine
US20040107948A1 (en) * 2002-12-06 2004-06-10 Meshenky Steven P. Tank manifold for internally mounted radial flow intercooler for a combustion air charger
US20050081522A1 (en) * 2002-03-17 2005-04-21 Gottfried Raab Internal combustion engine having two-stage exhaust-driven supercharger and charge air cooling between low pressure and high pressure compressors
US20140086733A1 (en) * 2012-09-24 2014-03-27 Samsung Techwin Co., Ltd. Compressing system
US20150184539A1 (en) * 2011-05-11 2015-07-02 Dresser-Rand Company Compact compression system with integral heat exchangers
US20170328269A1 (en) * 2016-05-11 2017-11-16 Mahle Filter Systems Japan Corporation Turbocharger
CN112814926A (en) * 2020-12-30 2021-05-18 东方电气集团东方汽轮机有限公司 Indirect cooling type compressor
CN114876826A (en) * 2022-05-02 2022-08-09 烟台东德实业有限公司 Unilateral two-stage high-speed centrifugal air compressor and expander integrated system

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH215474A (en) * 1938-07-21 1941-06-30 Sulzer Ag Multi-stage, axially working turbo machine.
US2396484A (en) * 1944-07-24 1946-03-12 Allis Chalmers Mfg Co Intercooled compressing apparatus

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH215474A (en) * 1938-07-21 1941-06-30 Sulzer Ag Multi-stage, axially working turbo machine.
US2396484A (en) * 1944-07-24 1946-03-12 Allis Chalmers Mfg Co Intercooled compressing apparatus

Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3056539A (en) * 1958-02-03 1962-10-02 Pullin Cyril George Gas turbine compressor units
US3209536A (en) * 1960-04-04 1965-10-05 Ford Motor Co Re-expansion type gas turbine engine with intercooler fan driven by the low pressure turbine
DE1120817B (en) * 1960-06-17 1961-12-28 Escher Wyss Ag Pre- or intermediate cooler of a gas turbine plant
US3211362A (en) * 1963-04-05 1965-10-12 Int Harvester Co Turbochargers
US3795458A (en) * 1971-01-20 1974-03-05 Bbc Sulzer Turbomaschinen Multistage compressor
US3892499A (en) * 1972-07-13 1975-07-01 Sulzer Ag Multistage turbocompressor having an intermediate cooler
US4125345A (en) * 1974-09-20 1978-11-14 Hitachi, Ltd. Turbo-fluid device
JPS5286707U (en) * 1975-12-24 1977-06-28
JPS5553757Y2 (en) * 1975-12-24 1980-12-12
US4431371A (en) * 1982-06-14 1984-02-14 Rockwell International Corporation Gas turbine with blade temperature control
US7191769B2 (en) * 2002-03-17 2007-03-20 Man Steyr Ag Internal combustion engine having two-stage exhaust-driven supercharger and charge air cooling between low pressure and high pressure compressors
US20050081522A1 (en) * 2002-03-17 2005-04-21 Gottfried Raab Internal combustion engine having two-stage exhaust-driven supercharger and charge air cooling between low pressure and high pressure compressors
US20040055740A1 (en) * 2002-09-20 2004-03-25 Meshenky Steven P. Internally mounted radial flow intercooler for a combustion air charger
US7278472B2 (en) 2002-09-20 2007-10-09 Modine Manufacturing Company Internally mounted radial flow intercooler for a combustion air changer
US20040062644A1 (en) * 2002-09-27 2004-04-01 Meshenky Steven P. Internally mounted radial flow intercooler for a rotary compressor machine
US6764279B2 (en) * 2002-09-27 2004-07-20 Modine Manufacturing Company Internally mounted radial flow intercooler for a rotary compressor machine
US20040107948A1 (en) * 2002-12-06 2004-06-10 Meshenky Steven P. Tank manifold for internally mounted radial flow intercooler for a combustion air charger
US6929056B2 (en) * 2002-12-06 2005-08-16 Modine Manufacturing Company Tank manifold for internally mounted radial flow intercooler for a combustion air charger
US20150184539A1 (en) * 2011-05-11 2015-07-02 Dresser-Rand Company Compact compression system with integral heat exchangers
US10012107B2 (en) * 2011-05-11 2018-07-03 Dresser-Rand Company Compact compression system with integral heat exchangers
US20140086733A1 (en) * 2012-09-24 2014-03-27 Samsung Techwin Co., Ltd. Compressing system
US20170328269A1 (en) * 2016-05-11 2017-11-16 Mahle Filter Systems Japan Corporation Turbocharger
US10215085B2 (en) * 2016-05-11 2019-02-26 Mahle Filter Systems Japan Corporation Turbocharger
CN112814926A (en) * 2020-12-30 2021-05-18 东方电气集团东方汽轮机有限公司 Indirect cooling type compressor
CN114876826A (en) * 2022-05-02 2022-08-09 烟台东德实业有限公司 Unilateral two-stage high-speed centrifugal air compressor and expander integrated system

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