US2543677A - Gas turbine plant - Google Patents

Gas turbine plant Download PDF

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Publication number
US2543677A
US2543677A US699562A US69956246A US2543677A US 2543677 A US2543677 A US 2543677A US 699562 A US699562 A US 699562A US 69956246 A US69956246 A US 69956246A US 2543677 A US2543677 A US 2543677A
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United States
Prior art keywords
circuit
turbine
compressor
air
pipe
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Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US699562A
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English (en)
Inventor
Traupel Walter
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Sulzer AG
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Sulzer AG
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Filing date
Publication date
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Publication of US2543677A publication Critical patent/US2543677A/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C1/00—Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid
    • F02C1/04—Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid the working fluid being heated indirectly
    • F02C1/08—Semi-closed cycles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/34—Gas-turbine plants characterised by the use of combustion products as the working fluid with recycling of part of the working fluid, i.e. semi-closed cycles with combustion products in the closed part of the cycle

Definitions

  • This invention relates to a gas turbine plant in which one part of the working medium iiows round in a circuit in which it is compressed in at least one compressor and expanded in at least one turbine, from which circuit a partial quantity of the working medium is continually withdrawn and expanded in at least two turbines, and into which circuit, as make-up for the working medium extracted, working medium is again in troduced through at least one compressor.
  • the invent/ion is characterised in that at least one turbine driving a compressor is fed by the part of the working medium flowing round in the circuit, and that at least one other turbine also driving a compressor, and the useful output turbine are fed by the part of the working medium taken from the circuit.
  • the turbines fed by the part of the working medium taken from the circuit are preferably arranged inlseries. It is also preferable to arrange the turbine driving a compressor before the ⁇ turbine producing useful Work. Between the compressor turbine and the useful work turbine a gas heater may be arranged which is formed for example as a combustion chamber in which fuel is consumed with the help of the oxygen contained in the working medium extracted from the circuit.
  • Fig. 1 illustrates diagrammatically a gas turbine plant according to the invention
  • Fig. 2 similarly illustrates a plant equipped with certain refinements which lead to an improvement with regard to efficiency, regulating possibilities and space requirements;
  • Fig. 3 similarly illustrates a plant in which the turbines which are fed with working medium extracted from the circuit are arranged in the opposite order;
  • Fig. 4 similarly illustrates a plant in which the turbine which is fed with the part of the working medium taken from the circuit drives a compressor in the circuit, whilst the compressor supplying the make-up air is driven by a circuit turbine.
  • the air compressed by compressors I and 2 with intermediate cooling in a cooler 3 is led partly through ⁇ pipe 4 to a heat exhanger 5 and partly through pipe 6 to another heat exchanger l.
  • the two heat exchangers 5 and 'I are arranged in parallel in the air current and function as preheaters, between which it is possible to arrange the distribution of the air by means of control member arranged in pipes 4 and 6 according to working conditions.
  • the two quantities of air unite in the preheated state in pipe 8 and are divided again into two parts at the spot 9.
  • One part ows through pipe I into the space surrounding the tubes II of a gas heater I2.
  • the gas expanded in the turbine 25 finally flows through pipe 21 into the heat exchanger 1, where, when flowing through the tubes 2B a part of its residual heat is transferred to the partial quantity of compressed air of thecircuit introduced through the pipe 6.
  • the combustion gas flows through pipe 29 to furthere points of use not shown in the drawing, for instance into a heat recuperator, or direct to atmosphere.
  • air is taken from the atmosphere through a compressor 30, compressed and introduced through pipe 3
  • the air is compressed to about 3 atmospheres gauge by the compressor 30, at
  • the air of the circuit is compressed to a final pressure of about 12 atmospheres gauge.
  • the air after being heated in the gas heater I2, flows into the turbine I 4 where it expands again to the original pressure of about 3 atmospheres gauge while doing work.
  • the compression ratio of the compressor 30 may be changed, for instance by changing the speed of the turbine 23.
  • the compressor will compressthe air to about 0.2 atmosphere gauge and at the highest overload to about 3.5 atmospheres gauge.
  • the highest pressures in the circuit then are 3 and 16 atmospheres gauge respectively at the outlet of the compressor 2.
  • the compression ratio in the circuit is consequently altered in the same manner with the altering of the output, the ratio being at low output considerably smaller than at a big output.
  • the regulating range may be considerably extended without having to put up with drawbacks of an economical nature. If it is possible to do without a, particularly high etliciency, the output of the plant may be still further increased by raising the pressure of the make-up air already at normal load to 4-5 atmospheres gauge for instance.
  • the turbine It fed with air in the circuit drives the circuit compressors I and 2.
  • an electric auxiliary machine 33 is also coupled, which comes into action as required either as a motor or as a generator and thus can be made use of when starting the plant and when compensating for a lack of output or an excess of output at the turbine I4.
  • the turbine 23, to which the combustion gas is rst fed, drives the compressor 36 introducing the make-up air into the circuit.
  • the useful output turbine 25 drives through the gear 34 the ships screw 35, which is arranged as an adjustable propeller.
  • two compressors 36 and 31 are adapted for introducing make-up air into the circuit. Between the compressors at least a part of the compression heat is withdrawn from the partly compressed air in a cooler 38. In this manner the pressure level of the circuit can be considerably raised.
  • the pressure of the air introduced into the circuit through the pipe 3I may for instance amount to 5 atmospheres gauge or even more, whilst the maximum pressure at the outlet from the circuit compressor 2 amounts to about 20 atmospheres gauge and more.
  • the output of the plant may thus be varied within a big range. It is for instance possible with good eiciencies to obtain an overload which is up to 8 times greater than the normal load.
  • a further improvement is obtained by introducing the air preheated in the heat exchanger I through the pipe 39 to the spot in the heat exchanger 5 where the same temperature prevails as at the outlet from the heat exchanger 'I. In this manner it is possible to preheat to the same high temperature the part of the circuit air owing through the pipe 4 and also the part of the circuit air flowing through the pipe 6 and thereby recover again the maximum quantity ci waste heat. Plants as shown in Fig. 2 are particularly suitable for cases Where big outputs have to be installed in limited spaces and high efficiencies must be obtained, for instance for the propulsion of ships, especially warships.
  • the combustion gas from the gas heater I2 is fed iirst of all to the useful output turbine 25 and only after that to the compressor turbine 23. In this manner it is possible in certain cases to obtain a simplification of the regulating. Likewise one may do without intermediate heating of the combustion gas between the two turbines.
  • a gas turbine plant of the type which includes a working medium circuit having a compressor and a turbine therein, two turbines driven by working medium extracted from said ⁇ circuit, and a compressor introducing make-up working medium into said circuit.
  • the improvement which comprises arranging the turbo machines of the plant in three sets, each set having one shaft, one of said sets including circuit turbine and circuit compressor, a second set including make-up compressor and an extraction turbine, and the third set including the plant external load and another extraction turbine, said extraction turbines being arranged in series in the ilow of extracted working medium.
  • a gas turbine plant according to claim 2 in which a gas heater is arranged to heat the working medium flowing from the turbine driving the make-up compressor to the turbine driving the plant load.
  • a gas turbine plant in which the gas heater is of the type including a combustion chamber in which fuel is burned by residual oxygen in the working medium heated.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
US699562A 1945-12-22 1946-09-26 Gas turbine plant Expired - Lifetime US2543677A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH248930T 1945-12-22

Publications (1)

Publication Number Publication Date
US2543677A true US2543677A (en) 1951-02-27

Family

ID=4467231

Family Applications (1)

Application Number Title Priority Date Filing Date
US699562A Expired - Lifetime US2543677A (en) 1945-12-22 1946-09-26 Gas turbine plant

Country Status (6)

Country Link
US (1) US2543677A (de)
CH (1) CH248930A (de)
DE (1) DE843770C (de)
ES (1) ES174674A1 (de)
FR (1) FR937775A (de)
GB (1) GB619114A (de)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2986882A (en) * 1955-06-27 1961-06-06 Vladimir H Pavlecka Sub-atmospheric gas turbine circuits
US3232052A (en) * 1962-12-28 1966-02-01 Creusot Forges Ateliers Power producing installation comprising a steam turbine and at least one gas turbine
US6672062B2 (en) * 2001-12-21 2004-01-06 Caterpillar Inc Multi-stage supercharger arrangement with cross flow
US20090211260A1 (en) * 2007-05-03 2009-08-27 Brayton Energy, Llc Multi-Spool Intercooled Recuperated Gas Turbine
US20100288571A1 (en) * 2009-05-12 2010-11-18 David William Dewis Gas turbine energy storage and conversion system
US20110215640A1 (en) * 2010-03-02 2011-09-08 Icr Turbine Engine Corporation Dispatchable power from a renewable energy facility
US8669670B2 (en) 2010-09-03 2014-03-11 Icr Turbine Engine Corporation Gas turbine engine configurations
US8984895B2 (en) 2010-07-09 2015-03-24 Icr Turbine Engine Corporation Metallic ceramic spool for a gas turbine engine
US9051873B2 (en) 2011-05-20 2015-06-09 Icr Turbine Engine Corporation Ceramic-to-metal turbine shaft attachment
US10094288B2 (en) 2012-07-24 2018-10-09 Icr Turbine Engine Corporation Ceramic-to-metal turbine volute attachment for a gas turbine engine

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE941101C (de) * 1953-01-20 1956-04-05 Licentia Gmbh Verfahren zum Betrieb eines Erhitzers von beliebigen Stoffen mit einer Feuerung fuer beliebige Brennstoffe
DE1242525B (de) * 1963-03-28 1967-06-22 Res & Dev Pty Ltd Ruehrwerksflotationszelle mit einem um eine hohle vertikale Achse drehbaren Rotor

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2225311A (en) * 1936-12-15 1940-12-17 Milo Ab Gas turbine system
CH215484A (de) * 1939-11-17 1941-06-30 Sulzer Ag Gasturbinenanlage.
US2298663A (en) * 1939-06-28 1942-10-13 Suizer Freres Sa Gas turbine plant
US2312605A (en) * 1938-12-24 1943-03-02 Sulzer Ag Gas turbine plant
GB562251A (en) * 1941-12-17 1944-06-23 Sulzer Ag Improvements in or relating to gas turbine plants

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2225311A (en) * 1936-12-15 1940-12-17 Milo Ab Gas turbine system
US2312605A (en) * 1938-12-24 1943-03-02 Sulzer Ag Gas turbine plant
US2298663A (en) * 1939-06-28 1942-10-13 Suizer Freres Sa Gas turbine plant
CH215484A (de) * 1939-11-17 1941-06-30 Sulzer Ag Gasturbinenanlage.
GB562251A (en) * 1941-12-17 1944-06-23 Sulzer Ag Improvements in or relating to gas turbine plants

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2986882A (en) * 1955-06-27 1961-06-06 Vladimir H Pavlecka Sub-atmospheric gas turbine circuits
US3232052A (en) * 1962-12-28 1966-02-01 Creusot Forges Ateliers Power producing installation comprising a steam turbine and at least one gas turbine
US6672062B2 (en) * 2001-12-21 2004-01-06 Caterpillar Inc Multi-stage supercharger arrangement with cross flow
US20090211260A1 (en) * 2007-05-03 2009-08-27 Brayton Energy, Llc Multi-Spool Intercooled Recuperated Gas Turbine
US8499874B2 (en) 2009-05-12 2013-08-06 Icr Turbine Engine Corporation Gas turbine energy storage and conversion system
US20100288571A1 (en) * 2009-05-12 2010-11-18 David William Dewis Gas turbine energy storage and conversion system
US8708083B2 (en) 2009-05-12 2014-04-29 Icr Turbine Engine Corporation Gas turbine energy storage and conversion system
US20110215640A1 (en) * 2010-03-02 2011-09-08 Icr Turbine Engine Corporation Dispatchable power from a renewable energy facility
US8866334B2 (en) 2010-03-02 2014-10-21 Icr Turbine Engine Corporation Dispatchable power from a renewable energy facility
US8984895B2 (en) 2010-07-09 2015-03-24 Icr Turbine Engine Corporation Metallic ceramic spool for a gas turbine engine
US8669670B2 (en) 2010-09-03 2014-03-11 Icr Turbine Engine Corporation Gas turbine engine configurations
US9051873B2 (en) 2011-05-20 2015-06-09 Icr Turbine Engine Corporation Ceramic-to-metal turbine shaft attachment
US10094288B2 (en) 2012-07-24 2018-10-09 Icr Turbine Engine Corporation Ceramic-to-metal turbine volute attachment for a gas turbine engine

Also Published As

Publication number Publication date
GB619114A (en) 1949-03-03
DE843770C (de) 1952-07-14
FR937775A (fr) 1948-08-26
CH248930A (de) 1947-05-31
ES174674A1 (es) 1946-12-01

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