US2489939A - Variable load gas turbine system - Google Patents
Variable load gas turbine system Download PDFInfo
- Publication number
- US2489939A US2489939A US653381A US65338146A US2489939A US 2489939 A US2489939 A US 2489939A US 653381 A US653381 A US 653381A US 65338146 A US65338146 A US 65338146A US 2489939 A US2489939 A US 2489939A
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- United States
- Prior art keywords
- turbine
- gas turbine
- pipe
- compressor
- working medium
- Prior art date
- 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
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- 239000007789 gas Substances 0.000 description 34
- 238000002485 combustion reaction Methods 0.000 description 8
- 238000000034 method Methods 0.000 description 4
- RLQJEEJISHYWON-UHFFFAOYSA-N flonicamid Chemical compound FC(F)(F)C1=CC=NC=C1C(=O)NCC#N RLQJEEJISHYWON-UHFFFAOYSA-N 0.000 description 2
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000003292 diminished effect Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 230000006698 induction Effects 0.000 description 1
- PSGAAPLEWMOORI-PEINSRQWSA-N medroxyprogesterone acetate Chemical compound C([C@@]12C)CC(=O)C=C1[C@@H](C)C[C@@H]1[C@@H]2CC[C@]2(C)[C@@](OC(C)=O)(C(C)=O)CC[C@H]21 PSGAAPLEWMOORI-PEINSRQWSA-N 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
Images
Classifications
-
- 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
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
- F02C6/18—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use using the waste heat of gas-turbine plants outside the plants themselves, e.g. gas-turbine power heat plants
Definitions
- the invention relates to a method of operating gas turbine plants, especially of the type in which an auxiliary turbine serving to drive the compressor is worked by a working medium which flows in a circuit and the main turbine serving to produce useful output is worked by a working medium which is led away from the circuit, and further relates to a plant for carrying out the method.
- the aim of the invention is to make possible the operation of a plant in such a way that it works, on the one hand, at highest efficiency during normal load, and can, on the other hand, develop multiples of this normal load with eificiencies that remain reasonable.
- a plant of this type is particularly of value in the propulsion of war vessels.
- the problem is solved by leading away the quantity of working medium exhausted from the plant at normal useful output through a heat exchanger, but at higher useful outputs through an exhaust gas turbine.
- the gas turbine plant is equipped with a heat exchanger, an exhaust gas turbine installed beyond the useful output turbine, and diverting means arranged in the piping from the useful output turbine to the exhaust gas turbine. By these diverting means, the exhaust gases from the useful output turbine are led to the heat exchanger at normal load and to the exhaust gas turbine at higher loads.
- the compressor I compresses the working medium flowing in from pipe 2, intermediate cooling during compression being effected in the cooler 3, and delivers it in a compressed state partly through pipe 4 into a heat exchanger 5 and partly through pipe 6 into a heat exchanger 1.
- the part of the working medium withdrawn from the circuit through pipe 6 passes through the heat exchanger 1 and pipe I6 as the combustion air for the burner ll of the gas heater Ill.
- the products of combustion flow through the tube system 9 and give thereby a part of their heat to the working medium coming from pipe 8. With diminished temperature, the products of combustion flow through pipe I8 into the useful output turbine I 9.
- the exhaust pipe 20 from the useful output turbine has diverting means consisting of two valves 2
- the exhaust gas from the useful output turbine I9 then flows either through the space surrounding the tube system 24 or through the exhaust gas turbine 23 into the outlet pipe 25.
- air is led to the plant through pipe 26.
- This air can, depending on the setting of diverting means consisting of two valves 21 and 28, either be taken direct from the atmosphere through pipe 29 or supplied by the precompressor 3
- receives air for its part from the atmosphere through pipe 32. While being compressed, this air passes through an intermediate cooler 33.
- Turbine l2 which is worked with pure air, drives the circuit compressor I.
- an electric machine 34 is also coupled, with the help of which the plant can be started, any lack of energy during service made up or superfluous energy led away.
- the output of the useful output turbine I9 is transmitted to the ships propeller 31 through the gear 35 and the shaft 36.
- is driven by the exhaust turbine 23.
- the plant described is particularly suitable for the propulsion of warships.
- the separate machines and heat exchangers are designed in such a way that the maximum efliciency is obtained at an output intended for cruising speed.
- the dithus works aaepsc verting means consisting 01' valves 2
- the air freshly introduced into the circuit as make-up for the exhausted working medium is introduced into the plant direct from the atmosphere through pipes 29 and 29.
- valves 22 and 29 are opened and valves 21 and 2? closed.
- the exhaust gases from'the useful output turbine 19 consequently flow through the exhaust gas turbine 23 into the exhaust pipe 25.
- the exhaust gas turbine drives the compressor 38 which draws in air from the atmosphere through pipe 32 and delivers it into the circuit, in a more or less highly compressed state, through pipe 313 and opened valve 28.
- the useful output of the plant can be increased to a multiple of the normal output-for instance to 540 times that value-and reasonable efiiciencies can still be obtained.
- an emciency up to about 28% at normal load can be reached, and at full load of 8 times as much normal output, still about 26%.
- a gas turbine plant that includes, in comination, a main compressor, an internal-load turbine driving said compressor, a gas heater, a conduit connecting the outlet from said compressor to the inlet to said turbine through said surrounding thetube system 24 of the heat exchanger I and intothe exhaust pipe 25.
- combustion air heater intended for the gas heater I is combustion air heater, a conduit connecting the outlet from said turbine to the inlet to said compressor, a first branch conduit supplying combustion air to said gas heater from said compressor outlet, 9.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
Description
Nov. 29, 1949 w. TRAUPEL 2,489,939
VARIABLE LOAD GAS TURBINE SYSTEM Filed March 9, 1946 XNVENTOR W ER firm amen, BY
, the circuit is preheated in Patented Nov. 29, 1949 VARIABLE LOAD GAS TURBINE SYSTEM Walter Traupel, Winterthur, Switzerland, assignor to Sulzer Freres, Soclete Anonyme, Winterthur, Switzerland Application March 9, 1946, Serial No. 653,381
' In Switzerland May 5, 1945 3 Claims.
The invention relates to a method of operating gas turbine plants, especially of the type in which an auxiliary turbine serving to drive the compressor is worked by a working medium which flows in a circuit and the main turbine serving to produce useful output is worked by a working medium which is led away from the circuit, and further relates to a plant for carrying out the method.
The aim of the invention is to make possible the operation of a plant in such a way that it works, on the one hand, at highest efficiency during normal load, and can, on the other hand, develop multiples of this normal load with eificiencies that remain reasonable. A plant of this type is particularly of value in the propulsion of war vessels.
According to the invention, the problem is solved by leading away the quantity of working medium exhausted from the plant at normal useful output through a heat exchanger, but at higher useful outputs through an exhaust gas turbine. For carrying out this method, the gas turbine plant is equipped with a heat exchanger, an exhaust gas turbine installed beyond the useful output turbine, and diverting means arranged in the piping from the useful output turbine to the exhaust gas turbine. By these diverting means, the exhaust gases from the useful output turbine are led to the heat exchanger at normal load and to the exhaust gas turbine at higher loads. It is preferable, at normal load, to preheat, by means of this heat exchanger, the combustion air intended for the gas heater of the plant, but at higher loads to drive, by means of this exhaust gas turbine, a compressor to supply the plant with fresh working medium at increased pressure as make-up for the working medium withdrawn from the circuit.
The invention is further explained by reference to the drawing which illustrates, in simplified form, a preferred arrangement of a gas turbine plant for carrying out the disclosed method.
The compressor I compresses the working medium flowing in from pipe 2, intermediate cooling during compression being effected in the cooler 3, and delivers it in a compressed state partly through pipe 4 into a heat exchanger 5 and partly through pipe 6 into a heat exchanger 1.
The part of the working medium retained in heat exchanger 5 and flows through pipe 8 into the space surrounding the tube system 9 of the gas heater III. This working medium, thus heated, then flows through pipe II into the turbine I2, and, after expanding in the turbine, passes through pipe l3 into the tube system II of the heat exchanger 5. Here, a part of the heat still contained in the expanded working medium is transmitted to the working medium arriving through pipe 4 from the compressor I. A further part of the residual heat is withdrawn from the working medium in cooler I5. After this recooling, the working medium passes through pipe 2 again into the compressor I, where the circuit described begins anew.
The part of the working medium withdrawn from the circuit through pipe 6 passes through the heat exchanger 1 and pipe I6 as the combustion air for the burner ll of the gas heater Ill. The products of combustion flow through the tube system 9 and give thereby a part of their heat to the working medium coming from pipe 8. With diminished temperature, the products of combustion flow through pipe I8 into the useful output turbine I 9. The exhaust pipe 20 from the useful output turbine has diverting means consisting of two valves 2| and 22, by means of which the exhaust gas from the useful output turbine I9 can be led as desired either to the heat exchanger 1 or to the exhaust gas turbine 23. The exhaust gas from the useful output turbine I9 then flows either through the space surrounding the tube system 24 or through the exhaust gas turbine 23 into the outlet pipe 25.
As make-up for the working medium with-. drawn from the circuit, air is led to the plant through pipe 26. This air can, depending on the setting of diverting means consisting of two valves 21 and 28, either be taken direct from the atmosphere through pipe 29 or supplied by the precompressor 3| through pipe 30 in a precompressed state. The compressor 3| receives air for its part from the atmosphere through pipe 32. While being compressed, this air passes through an intermediate cooler 33.
Turbine l2, which is worked with pure air, drives the circuit compressor I. To the set consisting of the turbine I2 and the compressor I, an electric machine 34 is also coupled, with the help of which the plant can be started, any lack of energy during service made up or superfluous energy led away. The output of the useful output turbine I9 is transmitted to the ships propeller 31 through the gear 35 and the shaft 36. The compressor 3| is driven by the exhaust turbine 23.
The plant described is particularly suitable for the propulsion of warships. The separate machines and heat exchangers are designed in such a way that the maximum efliciency is obtained at an output intended for cruising speed. The dithus works aaepsc verting means consisting 01' valves 2|, 2!, 21 and 28 are then adjusted as shown in the drawing.
The exhaust gases from the useful output turbine I9 flow through the space preheated and residual heat in the working medium being exhausted from the plant is to a large extent recuperated. The air freshly introduced into the circuit as make-up for the exhausted working medium is introduced into the plant direct from the atmosphere through pipes 29 and 29. The plant with low pressure level in the circuit, for which the form of the blades and the crosssectional areas of flow of the machines are designed, so that a very high efliciency is ensured.
For increasing the output, valves 22 and 29 are opened and valves 21 and 2? closed. The exhaust gases from'the useful output turbine 19 consequently flow through the exhaust gas turbine 23 into the exhaust pipe 25. The exhaust gas turbine drives the compressor 38 which draws in air from the atmosphere through pipe 32 and delivers it into the circuit, in a more or less highly compressed state, through pipe 313 and opened valve 28. In this manner the useful output of the plant can be increased to a multiple of the normal output-for instance to 540 times that value-and reasonable efiiciencies can still be obtained. With the plant shown, an emciency up to about 28% at normal load can be reached, and at full load of 8 times as much normal output, still about 26%. a
I claim:
1. In a gas turbine plant that includes, in comination, a main compressor, an internal-load turbine driving said compressor, a gas heater, a conduit connecting the outlet from said compressor to the inlet to said turbine through said surrounding thetube system 24 of the heat exchanger I and intothe exhaust pipe 25. In this way, intended for the gas heater I is combustion air heater, a conduit connecting the outlet from said turbine to the inlet to said compressor, a first branch conduit supplying combustion air to said gas heater from said compressor outlet, 9. second branch conduit leading make-up air to said compressor inlet, and an external-load turbine driven by combustion products from said gas heater, the improvement that includes a heat exchanger arranged to heat plant working medium, a conduit supplying said heat exchanger exhaust gas from said external-load turbine as heating fluid, an exhaust gas turbine, a conduit supplying said exhaust gas turbine with exhaust gas as working medium, and diverting means controlling said two last mentioned conduits for diverting exhaust gas between said heat exchanger and said exhaust gas turbine.
2. The improvement of claim 1 in which the heat exchanger is arranged to heat combustion air in the first branch conduit.
3. The improvement of claim 1 in which an auxiliary compressor is driven by the exhaust gas turbine, a conduit connects the outlet of said auxiliary compressor to the second branch conduit, an intake from the atmosphere opens directly into said second branch conduit, and diverting means control the diverting of make-up air induction between said auxiliary compressor and said intake.
WALTER TRAUPEL.
REFERENCES CITED The following references are of record in the file of this patent:
UNITED STATES PATENTS Number Name Date 2,095,991 Lysholm Oct. 19, 1937 2,115,112 Lysholm Apr. 26, 1938
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CH2489939X | 1945-05-05 |
Publications (1)
Publication Number | Publication Date |
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US2489939A true US2489939A (en) | 1949-11-29 |
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Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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US653381A Expired - Lifetime US2489939A (en) | 1945-05-05 | 1946-03-09 | Variable load gas turbine system |
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Cited By (19)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2713245A (en) * | 1952-11-24 | 1955-07-19 | Austin Motor Co Ltd | Internal combustion turbine power plants with regenerative exhaust treatment system |
US2793019A (en) * | 1951-09-06 | 1957-05-21 | Bbc Brown Boveri & Cie | Gas turbine installation for the generation of hot compressed air |
US2845776A (en) * | 1954-07-30 | 1958-08-05 | Sulzer Ag | Gas turbine driven plant for supplying compressed air |
US2859954A (en) * | 1951-06-08 | 1958-11-11 | Power Jets Res & Dev Ltd | Gas turbine plant for providing a continuous supply of hot compressed air |
US3161020A (en) * | 1963-04-18 | 1964-12-15 | Mechanical Tech Inc | Centrifugal compressing of low molecular weight gases |
US5023505A (en) * | 1989-12-20 | 1991-06-11 | Gte Products Corporation | Electric lamp with improved frame support and method of producing same |
US5081832A (en) * | 1990-03-05 | 1992-01-21 | Rolf Jan Mowill | High efficiency, twin spool, radial-high pressure, gas turbine engine |
US5377483A (en) * | 1993-07-07 | 1995-01-03 | Mowill; R. Jan | Process for single stage premixed constant fuel/air ratio combustion |
US5572862A (en) * | 1993-07-07 | 1996-11-12 | Mowill Rolf Jan | Convectively cooled, single stage, fully premixed fuel/air combustor for gas turbine engine modules |
US5613357A (en) * | 1993-07-07 | 1997-03-25 | Mowill; R. Jan | Star-shaped single stage low emission combustor system |
US5628182A (en) * | 1993-07-07 | 1997-05-13 | Mowill; R. Jan | Star combustor with dilution ports in can portions |
US5638674A (en) * | 1993-07-07 | 1997-06-17 | Mowill; R. Jan | Convectively cooled, single stage, fully premixed controllable fuel/air combustor with tangential admission |
US5924276A (en) * | 1996-07-17 | 1999-07-20 | Mowill; R. Jan | Premixer with dilution air bypass valve assembly |
US6220034B1 (en) | 1993-07-07 | 2001-04-24 | R. Jan Mowill | Convectively cooled, single stage, fully premixed controllable fuel/air combustor |
US6735951B2 (en) * | 2002-01-04 | 2004-05-18 | Hamilton Sundstrand Corporation | Turbocharged auxiliary power unit with controlled high speed spool |
US6925809B2 (en) | 1999-02-26 | 2005-08-09 | R. Jan Mowill | Gas turbine engine fuel/air premixers with variable geometry exit and method for controlling exit velocities |
US11564288B2 (en) | 2018-07-25 | 2023-01-24 | Heat X, LLC | Magnetic induction style furnace or heat pump or magnetic refrigerator having combination conductive and heated or cooled fluid redirecting rotational plate |
US11564290B2 (en) | 2018-07-25 | 2023-01-24 | Heat X, LLC | Magnetic induction style furnace or heat pump incorporating forced air or fluid blowers |
US11564289B2 (en) | 2018-07-25 | 2023-01-24 | Heat X, LLC | Magnetic induction style furnace or heat pump with variable blower functionality including retractable magnet arrays |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2095991A (en) * | 1933-03-08 | 1937-10-19 | Milo Ab | Gas turbine system of the continuous combustion type |
US2115112A (en) * | 1933-02-01 | 1938-04-26 | Milo Ab | Gas turbine system |
-
1946
- 1946-03-09 US US653381A patent/US2489939A/en not_active Expired - Lifetime
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2115112A (en) * | 1933-02-01 | 1938-04-26 | Milo Ab | Gas turbine system |
US2095991A (en) * | 1933-03-08 | 1937-10-19 | Milo Ab | Gas turbine system of the continuous combustion type |
Cited By (22)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2859954A (en) * | 1951-06-08 | 1958-11-11 | Power Jets Res & Dev Ltd | Gas turbine plant for providing a continuous supply of hot compressed air |
US2793019A (en) * | 1951-09-06 | 1957-05-21 | Bbc Brown Boveri & Cie | Gas turbine installation for the generation of hot compressed air |
US2713245A (en) * | 1952-11-24 | 1955-07-19 | Austin Motor Co Ltd | Internal combustion turbine power plants with regenerative exhaust treatment system |
US2845776A (en) * | 1954-07-30 | 1958-08-05 | Sulzer Ag | Gas turbine driven plant for supplying compressed air |
US3161020A (en) * | 1963-04-18 | 1964-12-15 | Mechanical Tech Inc | Centrifugal compressing of low molecular weight gases |
US5023505A (en) * | 1989-12-20 | 1991-06-11 | Gte Products Corporation | Electric lamp with improved frame support and method of producing same |
US5081832A (en) * | 1990-03-05 | 1992-01-21 | Rolf Jan Mowill | High efficiency, twin spool, radial-high pressure, gas turbine engine |
US5572862A (en) * | 1993-07-07 | 1996-11-12 | Mowill Rolf Jan | Convectively cooled, single stage, fully premixed fuel/air combustor for gas turbine engine modules |
US5765363A (en) * | 1993-07-07 | 1998-06-16 | Mowill; R. Jan | Convectively cooled, single stage, fully premixed controllable fuel/air combustor with tangential admission |
US5481866A (en) * | 1993-07-07 | 1996-01-09 | Mowill; R. Jan | Single stage premixed constant fuel/air ratio combustor |
US5377483A (en) * | 1993-07-07 | 1995-01-03 | Mowill; R. Jan | Process for single stage premixed constant fuel/air ratio combustion |
US5613357A (en) * | 1993-07-07 | 1997-03-25 | Mowill; R. Jan | Star-shaped single stage low emission combustor system |
US5628182A (en) * | 1993-07-07 | 1997-05-13 | Mowill; R. Jan | Star combustor with dilution ports in can portions |
US5638674A (en) * | 1993-07-07 | 1997-06-17 | Mowill; R. Jan | Convectively cooled, single stage, fully premixed controllable fuel/air combustor with tangential admission |
US5477671A (en) * | 1993-07-07 | 1995-12-26 | Mowill; R. Jan | Single stage premixed constant fuel/air ratio combustor |
US6220034B1 (en) | 1993-07-07 | 2001-04-24 | R. Jan Mowill | Convectively cooled, single stage, fully premixed controllable fuel/air combustor |
US5924276A (en) * | 1996-07-17 | 1999-07-20 | Mowill; R. Jan | Premixer with dilution air bypass valve assembly |
US6925809B2 (en) | 1999-02-26 | 2005-08-09 | R. Jan Mowill | Gas turbine engine fuel/air premixers with variable geometry exit and method for controlling exit velocities |
US6735951B2 (en) * | 2002-01-04 | 2004-05-18 | Hamilton Sundstrand Corporation | Turbocharged auxiliary power unit with controlled high speed spool |
US11564288B2 (en) | 2018-07-25 | 2023-01-24 | Heat X, LLC | Magnetic induction style furnace or heat pump or magnetic refrigerator having combination conductive and heated or cooled fluid redirecting rotational plate |
US11564290B2 (en) | 2018-07-25 | 2023-01-24 | Heat X, LLC | Magnetic induction style furnace or heat pump incorporating forced air or fluid blowers |
US11564289B2 (en) | 2018-07-25 | 2023-01-24 | Heat X, LLC | Magnetic induction style furnace or heat pump with variable blower functionality including retractable magnet arrays |
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