WO2017036431A1 - Équipement pour augmentation et amélioration du rendement de sortie de turbine à gaz - Google Patents

Équipement pour augmentation et amélioration du rendement de sortie de turbine à gaz Download PDF

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Publication number
WO2017036431A1
WO2017036431A1 PCT/CZ2015/000099 CZ2015000099W WO2017036431A1 WO 2017036431 A1 WO2017036431 A1 WO 2017036431A1 CZ 2015000099 W CZ2015000099 W CZ 2015000099W WO 2017036431 A1 WO2017036431 A1 WO 2017036431A1
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WO
WIPO (PCT)
Prior art keywords
gas turbine
inlet
compressor
compressed
primary
Prior art date
Application number
PCT/CZ2015/000099
Other languages
English (en)
Inventor
Marek OTEVŘEL
Original Assignee
Otevřel Marek
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Otevřel Marek filed Critical Otevřel Marek
Priority to GB1803289.6A priority Critical patent/GB2556011B/en
Priority to PCT/CZ2015/000099 priority patent/WO2017036431A1/fr
Publication of WO2017036431A1 publication Critical patent/WO2017036431A1/fr

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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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/10—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with another turbine driving an output shaft but not driving the compressor
    • C—CHEMISTRY; METALLURGY
    • C07—ORGANIC CHEMISTRY
    • C07D—HETEROCYCLIC COMPOUNDS
    • C07D498/00—Heterocyclic compounds containing in the condensed system at least one hetero ring having nitrogen and oxygen atoms as the only ring hetero atoms
    • C07D498/02—Heterocyclic compounds containing in the condensed system at least one hetero ring having nitrogen and oxygen atoms as the only ring hetero atoms in which the condensed system contains two hetero rings
    • C07D498/04—Ortho-condensed systems
    • 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
    • F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
    • F02C3/22—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure
    • 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
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output

Definitions

  • the invention concerns the equipment for the gas turbine output and/or efficiency increasing.
  • the equipment includes the compressor with impeller for the input medium compressing, combustion chamber for heating of the compressed input media, and the primary gas turbine with impeller driven by combustion gases from the combustion chamber, and power-connected with the primary compressor impeller, while for the purpose of compressed input medium heating the combustion chamber is provided with the fuel mixture inlet from the secondary system for the fuel mixture preparation by mixing of fuel with oxidizer.
  • the compressor-gas turbine set comprises further the chemical recuperator for preheating of the fuel mixture in the heat exchanger by outlet combustion gases of the gas turbine and thermo-chemical transformation of the fuel mixture formed by hydrocarbons and water vapour into a treated fuel mixture rich with hydrogen. Downstream the outlet of partly cooled output combustion gases from the chemical recuperator the steam generator, for further utilisation of output combustion gases waste heat by heating of water by these output combustion gases and its transformation into vapour, is arranged.
  • the steam exhaling from the steam generator is subsequently mixed with fuel, formed by hydrocarbons, into the fuel mixture of steam and hydrocarbons, which is brought to chemical recuperator for endothermic thermo-chemical treatment and the hydrogen-rich fuel mixture treated in this way is led further to the combustion chamber.
  • the objective of the solution according to the file No. US5386688 is to increase thermal efficiency of the gas turbine, to reduce temperature of combustion gases entering the gas turbine and in particular to prevent undesired combination of simultaneous high temperatures and high pressures, to utilise the gas turbine waste heat in the steam generator for production of steam, to treat the fuel mixture for combustion in the combustion chamber in such a way to improve combustion and to reduce content of detrimental substances in outlet combustion gases of the gas turbine.
  • the solution has the following disadvantages:
  • the low thermal efficiency of the gas turbine has to be compensated by a cascade of in parallel arranged sets of compressors for compressing of input air and gas turbines.
  • compressor for compressing of input air and gas turbine which will enable bigger thrust or power output of the gas turbine, respectively, controllable within wide range, and improvement of the gas turbine efficiency.
  • Further objective of the invention is a design of a jet engine or gas turbine, which will enable a higher total pressure ratio, or bigger difference between the compressor inlet pressure and at the turbine outlet pressure compared to comparable jet engines or gas turbines,
  • the secondary system for the fuel mixture preparation by mixing of fuel with oxidizer and possibly with other admixtures according to the invention, the substance of which consists in the fact, that the secondary system comprises the secondary gas generator with compressed fuel inlet, with compressed oxidizer inlet and with outlet of the partly combusted fuel mixture, connected with inlet of the secondary gas turbine, while the outlet of the secondary gas turbine is connected with the combustion chamber of the primary gas turbine and the shaft of the secondary gas turbine is power-connected with the power consumption equipment.
  • the secondary gas generator can be provided with injector of a suitable inert admixture (e.g. water or water steam) to increase volume of the resulting fuel mixture and/or reduction or control of temperature of the resulting fuel mixture .
  • a suitable inert admixture e.g. water or water steam
  • the shaft of the secondary gas turbine can be powered-connected with the shaft of the upstream primary compressor for compressing of the input medium, that outlet of which can be connected with the primary compressor inlet.
  • the line of compressed oxidizer can pass to the secondary gas generator inlet through the heat exchanger for cooling of the input medium upstream the inlet into the primary compressor and/or the line of compressed fuel can pass to the secondary gas generator inlet through the heat exchanger for cooling of outlet gases of the primary driving turbine.
  • the shaft of the secondary gas turbine can be powered-connected with the shaft of the secondary compressor for compressing of the oxidizer, while the secondary compressor inlet can be connected with the outlet of the primary compressor and the outlet of the secondary compressor can be connected with the inlet of the compressed oxidizer into the secondary gas generator .
  • the compressed fuel line can pass to the secondary gas generator inlet through the heat exchanger for cooling of the line between the outlet of the primary compressor and inlet of the secondary compressor for compressing of the oxidizer .
  • the line of the compressed oxidizer can pass to the inlet of the secondary gas generator or the line of the compressed fuel can pass to the inlet of the secondary gas generator through the heat exchanger for cooling of the input medium upstream inlet into the inlet primary compressor or through the heat exchanger.
  • the invention idea consists in combination of utilisation of the partly combusted hot air and the fuel -rich outlet from the separated gas generator in a single system, which results in increasing of the total pressure ratio, or in increasing of the difference between the compressor inlet pressure and the turbine outlet pressure.
  • modification of the jet engine or of the gas turbine such modification will result in increased thrust or output, respectively, or in the system total
  • the equipment for the gas turbine output increasing always consists of the primary "classic" subsystem of the gas turbine and secondary additional subsystem of the gas generator.
  • the primary subsystem utilises the surrounding gaseous media as the oxidizer and as a rule it works in the mode rich with oxidizer (in the lean-burn mode) with respect to temperature limitations of material.
  • That secondary subsystem utilises the compressed fuels in a form of compressed gases, compressed liquids or supercritical liquids, respectively.
  • the above fuels are preheated or partly combusted in the generator in the rich-burn mode, and subsequently expanded in the turbine.
  • the combustion gases rich with hydrogen and possibly other reduction gases are injected into the combustion chamber and/or into the
  • Output of the secondary subsystem can be utilised either for further compression of the primary air stream, e.g. by means of the low-pressure compressor, as shown in Figure 2, or also in other secondary auxiliary subsystems, requiring power input, possibly it can be utilised for
  • waste heat from the primary subsystem may be utilised with advantage for preheating or reforming
  • partially compressed primary flow of air can be pre-cooled by the secondary fuels, e.g. by means of a heat exchanger.
  • the system can be equipped with the fluid injection; e.g. of the oxidizer, inert admixture or their mixture; into the primary system before compression to the purpose of cooling of the brought air, or to further increase the thrust or the maximum operating ceiling, as provided e.g. in the file No. US6644015.
  • Liquidised air can be contemplated as the secondary oxidizer, with a triple benefit. First, it is the directly available source of oxygen, second, it may serve for precooling of the primary air flow e.g.
  • this system can be designed in such a way that it will need no extra starting system, if the gas generator subsystem has the self-start ability. Pressure increase in the primary system induced in those faces of compressing, which drive the secondary expansion equipment, can provide the sufficient pressure gradient for starting of the primary flow subsystem.
  • the advantage of the equipment for increase of output and improvement of efficiency of the gas turbine according to the invention consists in increased output and improved efficiency of the gas turbine and in the fact, that it utilises the gas generator products for partial compression in a phase of a low- pressure, intermediate-pressure or a high-pressure compression or in their arbitrary combination. Further advantage is
  • the equipment for increase of output and improvement of efficiency of the gas turbine includes the primary compressor 101 with impeller for the input medium compressing, combustion chamber 102 for heating of the
  • the outlet gases from the primary gas turbine 103 are led to the driving turbine 104, which mechanically drives the alternator 105.
  • the combustion chamber 102 is provided with the fuel mixture inlet from the secondary system 1 for preparation of the fuel mixture by mixing of fuel with the oxidizer.
  • the secondary system 1 includes the secondary gas generator 4 with inlet 41 of the compressed fuel, with inlet 42 of the compressed oxidizer and with outlet 43 of the partly combusted fuel mixture.
  • the outlet 43 of the partly combusted fuel mixture is connected with inlet of the secondary gas turbine 3.
  • the secondary gas turbine 3 is connected with the combustion chamber 102 of the primary gas turbine 101 and the shaft 31 of the secondary gas turbine 3 is power-connected with the ⁇ power consumption equipment, which is the alternator 8.
  • the liquid fuel is stored in liquid fuel storage tank 7, which is connected with the pressure pump 71, supplying the compressed fuel to inlet 41 of the secondary gas generator 4.
  • the liquid oxidizer is stored in storage tank 6, which is connected with the pressure pump 61, supplying the compressed oxidizer into inlet 42 of the secondary gas generator 4.
  • the fuel stored in the storage tank 7 is liquid one and before injection into the combustion chamber 102 of the gas turbine 103 it is first compressed to a high-pressure degree (1-100 MPa, more suitably to 5-50 MPa, even more suitably to 10-30 MPa) , partly combusted with the secondary oxidizer, supplied by the pressure pump 61 into the gas generator 4, which produces the reduction, fuel-rich gas mixture of necessary temperature, e.g. 600-2000 K or more suitably 900-1400 K, which is partly expanded in the secondary expansion turbine 3 to a pressure close to the operating pressure of the combustion chamber 102.
  • a high-pressure degree (1-100 MPa, more suitably to 5-50 MPa, even more suitably to 10-30 MPa
  • Fig. 1 Part of the enthalpic content, gas mixture, is delivered to the secondary expansion turbine 3 during expansion and subsequently utilised in alternator 8, which finally leads to increase of total efficiency and capacity of the system.
  • the arrangement according to Fig. 1 can be used advantageously for modernising of the already existing jet engine or gas turbine, in principle without the necessity of any principle modifications of the original equipment .
  • secondary system 1 similarly as in Fig. 1, includes the secondary gas generator 4 with inlet 41 of compressed fuel, with inlet 42 of compressed oxidizer and with outlet 43 of the partly combusted fuel mixture, connected with inlet of the secondary gas turbine 3.
  • the outlet of the secondary gas turbine 3 is connected with the combustion chamber 102 of the primary gas turbine 103.
  • Shaft 31 of the secondary gas turbine 3 is power- connected with the shaft 21 of the upstream primary compressor 2 for compression of the input medium, the outlet of which is connected with inlet of the primary compressor 101.
  • Fig. 2 can be utilised with a new or existing jet engine or gas turbine by installing of the pre- compression system and in this way it is possible to increase the capacity of the original equipment up to several times, together with increasing of the compression ratio and/or pressure at outlet from the primary turbine, which results in increased thermal efficiency of the system.
  • the fuel from storage tank 7 is first pressurised, partly combusted and expanded in a way, which was shown in Fig. 1.
  • the secondary gas turbine 3 is not driving the alternator, but the upstream primary compressor 2, which compresses the brought primary flow of air before it's entering the primary compressor 101.
  • the primary system 100 is the already used turbine, it has to be modified for higher values of absolute pressure, forces and force moments acting on the turbine components, however, the geometry, volumetric flow and pressure ratio may almost always remain without any change, only it is necessary to satisfy higher temperature of the air brought.
  • Fig. 3 which shows utilisation of compressed air as the secondary oxidiser
  • the shaft 32 of the secondary gas turbine 3 is power-connected with the shaft 221 of the secondary compressor 22 for compressing of the oxidiser, while the inlet of the secondary compressor 22 is connected with outlet of the primary compressor 101 and the outlet of the secondary
  • the compressor 22 is connected with inlet 42 of the compressed oxidiser into the secondary gas generator 4.
  • the equipment is provided with the system of heat exchange, formed by the heat exchangers 10-11, with the purpose to pre-cool the gaseous oxidiser, which is taken from the outlet of the primary compressor 101 and brought to inlet of the secondary compressor 22.
  • the line 72 of the compressed fuel passes through the first heat exchanger 10, in which the compressed fuel flowing through the line 72 cools down the heat carrier, which flows into the second heat exchanger 11, in which the heat carrier formed by the compressed fuel cools down the compressed inlet medium, which is taken from the outlet of the primary compressor 101 and brought to inlet of the secondary compressor 22.
  • Fig. 3 a smaller part of the outgoing primary air flow, compressed in the primary compressor 101 of the gas turbine 103, is further compressed in the high-pressure
  • the oxidiser which is the liquid air
  • the oxidiser pump 61 which brings the oxidiser into a high-pressure condition.
  • the compressed oxidiser line passes through the heat exchanger 12 for cooling down of the input medium upstream the inlet into the primary compressor 101.
  • the compressed oxidiser is led from the heat exchanger 12 further to oxidiser inlet 42 of the secondary gas generator 4.
  • the fuel taken from the liquid fuel storage tank 7 and compressed by the fuel pump 71, is led by the fuel line 72 into the heat exchanger 13 before it enters the inlet 41 of the secondary gas generator 4.
  • the oxidiser line 63 passes through the heat exchanger 13 before the oxidiser enters the inlet 42 of the secondary gas generator 4. Finally, through the heat exchanger 13 passes the outlet pipeline from the primary driving turbine 104, which pipeline is cooled down and thus the temperature of gases, going out from the driving turbine 104 into the ambient environment, is being reduced. According to Fig. 4 the equipment exploits fully potential of the idea in power engineering. As it was already mentioned, the liquid air offers itself as the secondary flow oxidiser, with a triple benefit.
  • the fuel is also preheated and possibly reformed in heat exchanger 13, before it is led into the secondary gas generator 4 for partial combustion with the secondary,
  • Fig. 5 shows the example connection of the secondary system in the aircraft driving unit or in a driving unit for a cosmic space plane.
  • the equipment according to Fig. 5 includes the secondary gas generator 4 with inlet 41 of compressed fuel, with inlet 42 of compressed oxidiser and with outlet 43 of the partly combusted fuel mixture, which is connected with inlet of the secondary gas turbine 3.
  • Outlet of the secondary gas turbine 3 is connected partly with the combustion chamber 102 of the primary gas turbine 103 and partly with inlet of further, additional secondary gas turbine 33.
  • the connection according to Fig. 5 can be considered a driving unit suitable in particular for supersonic, or hypersonic, respectively, military and civil space shuttles.
  • the on-board secondary propellants, fuel and secondary oxidiser are as always compressed to a value higher than the operating pressure of the combustion chamber 102, partly combusted in the rich-burn mode in the secondary gas generator 4 and subsequently expanded in the secondary gas turbine 3, which drives the low-pressure upstream primary compressor 23. Subsequently the secondary flow is divided.
  • One part is led into the combustion chamber 102 and the other part is further expanded in the additional secondary gas turbine 33, which drives the intermediate-pressure compressor 24 up to reaching of the operating pressure of the additional combustion chamber 106.
  • the additional combustion chamber 106 it meets the hot primary flow, as a rule rich with oxidiser, to the purpose of complete combustion and, if possible, with

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Organic Chemistry (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne un équipement qui permet d'augmenter la sortie et d'améliorer le rendement d'une turbine à gaz et qui comprend un compresseur primaire (101) ayant une hélice pour comprimer un milieu d'entrée, une chambre de combustion (102) pour chauffer le milieu d'entrée comprimé et une turbine à gaz primaire (103) ayant une hélice actionnée par des gaz de combustion venant de la chambre de combustion (102) et reliée en entraînement à l'hélice du compresseur primaire (101). Pour le chauffage du milieu d'entrée comprimé, la chambre de combustion (102) est pourvu d'une entrée d'un mélange de carburant provenant d'un système secondaire (1) pour la préparation du mélange de carburant par mélange du combustible avec un oxydant, et, selon l'invention, le système secondaire (1) comprend un générateur de gaz secondaire (4) ayant une entrée (41) du carburant comprimé, une entrée (42) de l'oxydant comprimé et une sortie (43) du mélange de carburant partiellement brûlé reliées à une entrée d'une turbine à gaz secondaire (3), la sortie de la turbine à gaz secondaire (3) étant reliée à la chambre de combustion (102) de la turbine à gaz primaire (103) et l'arbre (31) de la turbine à gaz secondaire (3) étant relié en entraînement à un équipement (2, 8, 22, 23, 24) pour la consommation d'énergie. De manière avantageuse, l'arbre (31) de la turbine à gaz secondaire (3) est relié en entraînement à un arbre (21) d'un compresseur primaire amont (2) pour la compression du milieu d'entrée, dont la sortie est reliée à l'entrée du compresseur primaire (101) ou à l'arbre (221) du compresseur secondaire (22) pour comprimer l'oxydant, alors que l'entrée du compresseur secondaire (22) est reliée à la sortie du compresseur primaire (101) et que la sortie du compresseur secondaire (22) est reliée à l'entrée (42) de l'oxydant comprimé dans le générateur de gaz secondaire (4).
PCT/CZ2015/000099 2015-08-31 2015-08-31 Équipement pour augmentation et amélioration du rendement de sortie de turbine à gaz WO2017036431A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB1803289.6A GB2556011B (en) 2015-08-31 2015-08-31 Equipment for gas turbine output increasing and efficiency improvement
PCT/CZ2015/000099 WO2017036431A1 (fr) 2015-08-31 2015-08-31 Équipement pour augmentation et amélioration du rendement de sortie de turbine à gaz

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/CZ2015/000099 WO2017036431A1 (fr) 2015-08-31 2015-08-31 Équipement pour augmentation et amélioration du rendement de sortie de turbine à gaz

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WO2017036431A1 true WO2017036431A1 (fr) 2017-03-09

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Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US586688A (en) 1897-07-20 Pump for acids or other liquids
US2592749A (en) * 1947-01-16 1952-04-15 Rateau Soc Gas turbine engine associated with a gas producer under pressure
US4058974A (en) * 1975-05-14 1977-11-22 Bbc Brown Boveri & Company Limited Combined gas/steam power plant with pressurized-gas generator
US4729217A (en) * 1984-01-31 1988-03-08 Bbc Brown, Boveri & Company, Limited Combined gas/steam power station plant
GB2229733A (en) * 1989-03-24 1990-10-03 Gen Electric Hydrocarbon combustion apparatus and method
US5386688A (en) 1993-04-23 1995-02-07 Cascaded Advanced Turbine Limited Partnership Method of generating power with high efficiency multi-shaft reheat turbine with interccooling and recuperation
WO1999014473A1 (fr) * 1997-09-12 1999-03-25 Texaco Development Corporation Chambre d'expansion de gaz de synthese situee immediatement en amont d'une turbine a gaz
US6644015B2 (en) 2001-10-29 2003-11-11 Hmx, Inc. Turbojet with precompressor injected oxidizer

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US586688A (en) 1897-07-20 Pump for acids or other liquids
US2592749A (en) * 1947-01-16 1952-04-15 Rateau Soc Gas turbine engine associated with a gas producer under pressure
US4058974A (en) * 1975-05-14 1977-11-22 Bbc Brown Boveri & Company Limited Combined gas/steam power plant with pressurized-gas generator
US4729217A (en) * 1984-01-31 1988-03-08 Bbc Brown, Boveri & Company, Limited Combined gas/steam power station plant
GB2229733A (en) * 1989-03-24 1990-10-03 Gen Electric Hydrocarbon combustion apparatus and method
US5386688A (en) 1993-04-23 1995-02-07 Cascaded Advanced Turbine Limited Partnership Method of generating power with high efficiency multi-shaft reheat turbine with interccooling and recuperation
WO1999014473A1 (fr) * 1997-09-12 1999-03-25 Texaco Development Corporation Chambre d'expansion de gaz de synthese situee immediatement en amont d'une turbine a gaz
US6644015B2 (en) 2001-10-29 2003-11-11 Hmx, Inc. Turbojet with precompressor injected oxidizer

Also Published As

Publication number Publication date
GB201803289D0 (en) 2018-04-11
GB2556011A (en) 2018-05-16
GB2556011B (en) 2021-02-24

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