WO1993018289A1 - Procede de conversion d'energie thermique en energie mecanique dans un moteur a turbine a gaz et moteur a turbine a gaz - Google Patents

Procede de conversion d'energie thermique en energie mecanique dans un moteur a turbine a gaz et moteur a turbine a gaz Download PDF

Info

Publication number
WO1993018289A1
WO1993018289A1 PCT/RU1992/000128 RU9200128W WO9318289A1 WO 1993018289 A1 WO1993018289 A1 WO 1993018289A1 RU 9200128 W RU9200128 W RU 9200128W WO 9318289 A1 WO9318289 A1 WO 9318289A1
Authority
WO
WIPO (PCT)
Prior art keywords
section
ρabοchegο τela
working body
source
engine
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.)
Ceased
Application number
PCT/RU1992/000128
Other languages
English (en)
Russian (ru)
Inventor
Anatoly Mikhailovich Rakhmailov
Vadim Arkadievich Kostinsky
Igor Leonidovich Drozd
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.)
Smeshannoe Tovarischestvo 'germes'
Original Assignee
Smeshannoe Tovarischestvo 'germes'
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 Smeshannoe Tovarischestvo 'germes' filed Critical Smeshannoe Tovarischestvo 'germes'
Publication of WO1993018289A1 publication Critical patent/WO1993018289A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

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
    • F02C3/34—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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • 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
    • F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
    • F02C3/145—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant the combustion chamber being in the reverse flow-type

Definitions

  • the invention is related to energy, and it is known that
  • the air is taken out of the atmosphere of the compressor and the compressor.
  • the combustion chamber 15 receives heat from a source of heat in the form of a combustion chamber, which supplies fuel.
  • the combustion chamber is divided into two flows, one of which is used for the actual combustion of fuel, and the other is used to reduce the consumption of food.
  • the resulting heated body is expanded to a degree of success, as a result of which a useful process is achieved.
  • the gas engine of the engine is partly used by the compressor, while the remaining part of the engine is of ample space.
  • the quantity of atmospheric air is also reduced, which is not necessary for the normal operation of the engine, and, correspondingly, it is reduced in gas.
  • the convenience of the working body is due to the use of the working body for the cooling of the working body of the process
  • the written method is available with a gas engine, which is at least two, which is located in the primary unit, which is more important, but is more Pe ⁇ vy v ⁇ d ezhe ⁇ a s ⁇ bschae ⁇ sya with is ⁇ chni ⁇ m nag ⁇ e ⁇ g ⁇ ⁇ ab ⁇ cheg ⁇ ⁇ ela, v ⁇ y v ⁇ d ezhe ⁇ a s ⁇ bschae ⁇ sya with vy ⁇ d ⁇ m ⁇ e ⁇ v ⁇ y ⁇ u ⁇ binn ⁇ y s ⁇ u ⁇ eni and vy ⁇ d ezhe ⁇ a s ⁇ bschae ⁇ sya with v ⁇ d ⁇ m ⁇ e ⁇ v ⁇ y ⁇ u ⁇ binn ⁇ y e ⁇ u ⁇ eni.
  • the invention has posed a problem to use in the process of converting process energy into a mechanical engine in a gas turbine
  • the task posed is solved by the fact that in the process of converting the thermal energy into mechanical energy in a gas-powered engine, which has a little other than a partial
  • thermodynamic system of the operation of the body includes the second stage of expansion, which is not ensured by the user.
  • thermodynamic system of the working body includes the second stage - 4 - ⁇ asshi ⁇ eniya, ⁇ susches ⁇ vlyaemuyu ne ⁇ s ⁇ eds ⁇ venn ⁇ ⁇ sle ⁇ ln ⁇ g ⁇ s ⁇ edineniya ⁇ a ⁇ ab ⁇ cheg ⁇ ⁇ ela with ⁇ m ⁇ ab ⁇ avsheg ⁇ ⁇ ab ⁇ cheg ⁇ ⁇ ela ⁇ u ⁇ binn ⁇ s ⁇ u ⁇ eni ⁇ e ⁇ ed ⁇ dache ⁇ ⁇ ab ⁇ cheg ⁇ ⁇ ela in ⁇ u ⁇ binnuyu s ⁇ u ⁇ en not ⁇ is ⁇ di ⁇ reduce ⁇ i-
  • thermodynamic system 15 of this output from a gas-powered engine, which significantly reduces the cost of engine operation. Otherwise, such a change in the thermodynamic system will reduce the quantity of pipe that is less than ⁇ by one.
  • the operating unit that has been operated has been disconnected from the power supply unit and the unit has been disconnected from the power supply unit.
  • the working body which has lost the working capacity, is relieved by simply removing energy from it, thereby removing the energy from the body. With this, the total number of SDPs is rising.
  • part of the source of the heated working body has an irregular part, which is connected with the initial part and has a part-time accident, and also an end-user part.
  • Part of the source part of the source of the working body has
  • the source of the heated working body is made in the form of rings for burning with an extracting device of its own, which is included in the supply.
  • the internal part of the Republic is communicated with by a simple part of the source of the primary operating condition due to an increase in the total cross-section of the total value.
  • the heating of the finished working body with the heated working body begins before mixing begins.
  • the process of changing the thermodynamic system of the working body is most intensified, which increases the total ⁇ PDP.
  • the engine may be equipped with a removable device, having inputs for a hotter and a cold outlet, communicating with an output device.
  • ⁇ Operations ⁇ - 7 - a good condition that is connected with the next one is progressive, and the other way out is with the other side - with the unit. With this, one way is possible to reduce the amount of working body that is provided for
  • the first method of operation increases the efficiency of the cooling of the working body and facilitates the increase of the engine’s DPS.
  • Fig. 2 is a schematic illustration of a gas-powered engine, in conjunction with a live invention in a separate version.
  • a gas-turbine ⁇ engine has a turbine degree I (which may be the only one or a step-by-step engine), the source of the oxidizer, for example, is airborne
  • Source 2 of the oxidizer is connected to the turbine stage of I shaft 4.
  • the gas turbine engine has a source of 5 heated, in addition to the
  • a source of 5 heated operation has a large device (not indicated), which is disconnected from the ignition source (3) - 8 - n ⁇ ). All of these devices are necessary for the formation of a hot mixture and its burning in order to create a source of 5 high temperature treatment in the source.
  • the output line of step I is connected to the line ⁇ C with
  • Source 5 of the heated working body has a section of 10 connections to the working bodies, the ⁇ line is connected ⁇ with the input of the step I.
  • thermodynamic state of the working body There is a change in the thermodynamic state of the working body. This change includes the first stage, which is carried out in the ⁇ zone, appropriately ⁇ to the primary part II of source 5 of the heated working body; the stage of mixing the flow of the heated body with the flow of the feed
  • the gas turbine ⁇ engine has turbine stages 1.12 and 13. Obviously, a number
  • step I 20 percent can be any and the engine may have only one step I, which is not relevant from the point of view of the result in this case. This is clearly visible in FIG. 2, source 5 of the working body was completed as the first main section II, ⁇ ⁇ ⁇ ⁇ ⁇ ⁇
  • ⁇ z ⁇ ne ⁇ , ⁇ imy ⁇ ayusche ⁇ ⁇ nachaln ⁇ mu uchas ⁇ u II is ⁇ chni ⁇ a 5 nag ⁇ e ⁇ g ⁇ ⁇ ab ⁇ cheg ⁇ ⁇ ela, ⁇ chnaya Part is ⁇ chni ⁇ a 5 nag ⁇ e ⁇ g ⁇
  • the direct narrowing 17 is used at the end of the 15th part, except for the narrowing of the 16th and 17th disconnection of the connection
  • Chain 8 which has a larger cross-section, is unused from the standby mode of heating, but the battery is open at the same time.
  • the heated working area has a cross-sectional area of 5–8 times larger than the integrated cross-sectional area.
  • the cross-section of the shaft is ⁇ 7, less
  • the oxidizer for example, air
  • the oxidizer is compressible ⁇ in the source of the oxidizing agent, for example, compressor 2, it runs on the channel uß ⁇ - I - it also supplies fuel (not indicated).
  • a quick work is started in the initial section II of source 5 on a heated working body when burning fuel with an unloading unit.
  • the products are well known to the experts and are not missing the present invention.
  • the other working body is expanded in the narrowing 16, due to which the kinetic energy of the high-throughput process of the working body is free of charge. Further, the heated working body moves around.
  • the integrated expansion in the narrowing 17 allows for the use of a free access to the device. - 12 - and a lively directional device (not specified) to ensure reliable and unharmed access to the drive to the other side of the road.
  • ⁇ ⁇ ezul- ⁇ a ⁇ e is ⁇ lz ⁇ vaniya ⁇ e ⁇ l ⁇ bmenn ⁇ g ⁇ us ⁇ s ⁇ va 21 snizhae ⁇ - 20 Xia ⁇ liches ⁇ v ⁇ ⁇ ab ⁇ avsheg ⁇ ⁇ ab ⁇ cheg ⁇ ⁇ ela, ⁇ davaem ⁇ g ⁇ for ⁇ lavdeniya nag ⁇ e ⁇ g ⁇ ⁇ ab ⁇ cheg ⁇ BODIES WHICH YOU ARE LOWING THE FRONT OF THE ENGINE.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)

Abstract

L'état thermodynamique du milieu actif introduit dans la partie turbine comprend sa détente puis son refroidissement par le milieu actif d'échappement de la partie turbine, avant son introduction dans cette dernière par mélange du flux de milieu actif au flux de milieu actif d'échappement de la partie turbine. Le procédé consiste à passer à la deuxième étape de détente immédiatement après mélange total du flux de milieu actif au flux de milieu actif d'échappement de la partie turbine, et avant acheminement du milieu actif dans la partie turbine. Dans un moteur à turbine à gaz, la partie de flux de la source (5) de milieu actif chauffé présente une partie initiale (11) reliée aux sources de combustible et d'oxydant, ainsi qu'une partie courbée (14) régulière reliée à la partie initiale (11), et dont la partie terminale (15) est voisine de la partie turbine (1). La partie courbée (14) présente deux cônes (16 et 17) dont un est situé dans la zone (E) voisine de la partie initiale (11), et l'autre se trouve avant la partie turbine, ainsi qu'une partie (10) dont la section transversale augmente entre lesdits cônes (16, 17) laquelle est reliée à la sortie de la partie turbine (1).
PCT/RU1992/000128 1992-03-09 1992-06-26 Procede de conversion d'energie thermique en energie mecanique dans un moteur a turbine a gaz et moteur a turbine a gaz Ceased WO1993018289A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
SU5026664 RU2031229C1 (ru) 1992-03-09 1992-03-09 Способ преобразования тепловой энергии в механическую в газотурбинном двигателе и газотурбинный двигатель
RU5026664 1992-03-09

Publications (1)

Publication Number Publication Date
WO1993018289A1 true WO1993018289A1 (fr) 1993-09-16

Family

ID=21596562

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/RU1992/000128 Ceased WO1993018289A1 (fr) 1992-03-09 1992-06-26 Procede de conversion d'energie thermique en energie mecanique dans un moteur a turbine a gaz et moteur a turbine a gaz

Country Status (2)

Country Link
RU (1) RU2031229C1 (fr)
WO (1) WO1993018289A1 (fr)

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4549402A (en) * 1982-05-26 1985-10-29 Pratt & Whitney Aircraft Of Canada Limited Combustor for a gas turbine engine
DE3425115A1 (de) * 1984-07-04 1986-01-16 Nebojsa Prof Dr Ing Gasparovic Gasturbinenanlage mit aufgeladenem, teilgeschlossenem kreislauf mit unmittelbarer verbrennung im arbeitsgasstrom
EP0269824A2 (fr) * 1986-11-25 1988-06-08 General Electric Company Brûleur combiné à diffusion et à prémélange pour veilleuse
US4914904A (en) * 1988-11-09 1990-04-10 Avco Corporation Oil cooler for fan jet engines

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4549402A (en) * 1982-05-26 1985-10-29 Pratt & Whitney Aircraft Of Canada Limited Combustor for a gas turbine engine
DE3425115A1 (de) * 1984-07-04 1986-01-16 Nebojsa Prof Dr Ing Gasparovic Gasturbinenanlage mit aufgeladenem, teilgeschlossenem kreislauf mit unmittelbarer verbrennung im arbeitsgasstrom
EP0269824A2 (fr) * 1986-11-25 1988-06-08 General Electric Company Brûleur combiné à diffusion et à prémélange pour veilleuse
US4914904A (en) * 1988-11-09 1990-04-10 Avco Corporation Oil cooler for fan jet engines

Also Published As

Publication number Publication date
RU2031229C1 (ru) 1995-03-20

Similar Documents

Publication Publication Date Title
EP1044321B1 (fr) Moteurs de turbine a gaz connectes en serie
US3971211A (en) Thermodynamic cycles with supercritical CO2 cycle topping
US5761896A (en) High efficiency method to burn oxygen and hydrogen in a combined cycle power plant
US5694761A (en) Combustor cooling for gas turbine engines
JP2698134B2 (ja) 燃焼放出物を制御する方法と放出物燃焼器
CA2452972C (fr) Methodes et systeme de production de poussee pour turbine a gaz
US20100000217A1 (en) Turbine engine with interstage heat
EP0379880A1 (fr) Méthode et système pour le refroidissement d'une turbine à gaz
US2930190A (en) Bypass gas turbine power plant employing regenerative cycle
US4382771A (en) Gas and steam generator
WO2005003533A2 (fr) Turbine a gaz a fort taux de compression, amelioree par rechauffe
WO1997014875A1 (fr) Dispositif de combustion refroidi regeneratuer pour turbine a gaz
GB2097476A (en) A method for using residue gas in gas turbines
US6176075B1 (en) Combustor cooling for gas turbine engines
EP1637712B1 (fr) Turbine à gaz avec un système à l'intérieur amélioré
RU2199020C2 (ru) Способ работы комбинированной газотурбинной установки системы газораспределения и комбинированная газотурбинная установка для его осуществления
WO1993018289A1 (fr) Procede de conversion d'energie thermique en energie mecanique dans un moteur a turbine a gaz et moteur a turbine a gaz
GB2289939A (en) Gas turbine and method of operating it
RU2031225C1 (ru) Способ преобразования тепловой энергии в механическую в газотурбинном двигателе и газотурбинный двигатель
RU2013614C1 (ru) Способ преобразования тепловой энергии в механическую в газотурбинном двигателе и газотурбинный двигатель для его осуществления
RU2006631C1 (ru) Способ работы высокотемпературного газотурбинного двигателя и высокотемпературный газотурбинный двигатель
US4578943A (en) Hydro-vapor free turbine engine
RU2044906C1 (ru) Способ преобразования тепловой энергии в механическую в газотурбинном двигателе и газотурбинный двигатель
RU2031226C1 (ru) Способ преобразования тепловой энергии в механическую в газотурбинном двигателе и газотурбинный двигатель
US5873233A (en) Method of operating a gas-turbine group

Legal Events

Date Code Title Description
AK Designated states

Kind code of ref document: A1

Designated state(s): JP KR US

AL Designated countries for regional patents

Kind code of ref document: A1

Designated state(s): AT BE CH DE DK ES FR GB GR IT LU MC NL SE

DFPE Request for preliminary examination filed prior to expiration of 19th month from priority date (pct application filed before 20040101)
122 Ep: pct application non-entry in european phase