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WO1993007370A1 - Procede de conversion d'energie thermique en energie mecanique dans un moteur a turbine a gas, et moteur a turbine a gas - Google Patents

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

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Publication number
WO1993007370A1
WO1993007370A1 PCT/SU1991/000198 SU9100198W WO9307370A1 WO 1993007370 A1 WO1993007370 A1 WO 1993007370A1 SU 9100198 W SU9100198 W SU 9100198W WO 9307370 A1 WO9307370 A1 WO 9307370A1
Authority
WO
WIPO (PCT)
Prior art keywords
engine
gas
turbine
appliance
source
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/SU1991/000198
Other languages
English (en)
Russian (ru)
Inventor
Anatoly Mikhailovich Rakhmailov
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'
Priority to PCT/SU1991/000198 priority Critical patent/WO1993007370A1/fr
Publication of WO1993007370A1 publication Critical patent/WO1993007370A1/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
    • F02C3/32—Inducing air flow by fluid jet, e.g. ejector action

Definitions

  • the invention is available for power, and the name for the process of converting thermal energy into a gas-powered engine and a gas-powered engine.
  • This method does not provide a sufficient increase in the PDA, since the multi-stage combustion of fuel does not reduce the amount of cooling gas. That, in
  • the gas engine is less than two, which is located at the lower end of the turbine unit, which is located on the 5th day of the week, and the source of the heated engine,
  • the appliance is taken from the compressor and discharged to the source of the heated work chamber as a camera
  • the food in the chamber is divided into two streams, one of the batteries is used for the actual unloading of the fuel, and the other is used to reduce the temperature of the food.
  • the resulting heated other body is expanding.
  • the gas engine of the engine is partly accessible to the compressor, and the remaining part of the engine is a useful engine.
  • the utility capacity of the gas-turbine engine is comparable
  • this gas-powered outboard engine 25 and a small useful capacity, comprising a maximum of 4 ⁇ % of the capacity developed by the tubular steps.
  • the main disadvantages of this gas-powered outboard engine are low APD and low utility capacity. Otherwise, this engine will be emitted into the vehicle.
  • the basic task of the invention is to use the process of converting thermal energy into mechanical energy.
  • v ⁇ v ⁇ emya changes ⁇ e ⁇ m ⁇ dinamiches ⁇ e s ⁇ s ⁇ yaniya vv ⁇ dim ⁇ g ⁇ in ⁇ u ⁇ binnuyu s ⁇ u ⁇ en ⁇ ab ⁇ cheg ⁇ ⁇ ela, ⁇ ab ⁇ chee ⁇ el ⁇ , ⁇ davaem ⁇ e ⁇ at me ⁇ e in ⁇ e ⁇ vuyu ⁇ u ⁇ binnuyu s ⁇ u ⁇ en, d ⁇ vv ⁇ da therein • ⁇ asshi ⁇ yayu ⁇ and za ⁇ uchivayu ⁇ ⁇ n ⁇ si ⁇ eln ⁇ ⁇ d ⁇ ln ⁇ y ⁇ si
  • P ⁇ s ⁇ avlennaya task ⁇ a ⁇ zhe ⁇ eshae ⁇ sya ⁇ em, ch ⁇ gaz ⁇ - ⁇ u ⁇ binny dviga ⁇ el, s ⁇ de ⁇ zhaschy ⁇ at me ⁇ e two ⁇ azmeschennye in ⁇ chn ⁇ y chas ⁇ i ⁇ u ⁇ binnye s ⁇ u ⁇ eni and 25 used ⁇ chni ⁇ nag ⁇ e ⁇ g ⁇ ⁇ ab ⁇ cheg ⁇ ⁇ ela in s ⁇ ve ⁇ s ⁇ vii with iz ⁇ b- ⁇ e ⁇ eniem, provided ezhe ⁇ m having two v ⁇ da and vy ⁇ d, ⁇ i e ⁇ m ⁇ e ⁇ vy v ⁇ d ezhe ⁇ a s ⁇ bschae ⁇ eya with is ⁇ chni ⁇ m nag ⁇ e ⁇ g ⁇ ⁇ ab ⁇ cheg ⁇ ⁇ ela, v ⁇ y v ⁇ d ezhe ⁇ a s ⁇
  • the outlet of the first stage of the process is predominantly completed with a chamber, which is communicated with the second input of the ejector.
  • This camera provides an effective fence for the 0 working body at the exit from the first step of the process, an actual function.
  • the ring is installed on the side of the ring
  • each plate is located at a corner to the diameter of the cross-section of the ring channel.
  • FIG. 2 is a schematic illustration of a gas-powered engine, in accordance with the present invention, in a separate section;
  • FIG. 3 is a schematic illustration of a variant of a gas turbine engine with another embodiment of an electric engine, in conjunction with a present invention;
  • ⁇ ⁇ aches ⁇ ve is ⁇ ch- ni ⁇ a I nag ⁇ e ⁇ g ⁇ ⁇ ab ⁇ cheg ⁇ ⁇ ela is ⁇ lzue ⁇ sya ⁇ ame ⁇ a sg ⁇ - ⁇ aniya in ⁇ uyu ⁇ s ⁇ u ⁇ ae ⁇ ⁇ isli ⁇ el, na ⁇ ime ⁇ , v ⁇ zdu ⁇ ⁇ ⁇ m ⁇ ess ⁇ a 3 ⁇ a ⁇ ⁇ azan ⁇ s ⁇ el ⁇ y ⁇ , and ⁇ liv ⁇ , ⁇ a ⁇ ⁇ azan ⁇ in e ⁇ el ⁇ y.
  • Source I mixes 35 fuels and a precursor with a known method that does not have a source of ignition; - 7 - ctv (not shown). We want a warm, working body ,. It is simpler from source I to power 2, as shown by a simple C in FIG.
  • 25 may be missing, since some of the kinetic energy is missing and the body is used for expansion and shutdown.
  • FIG. 2 a schematic diagram is provided.
  • Gas engine in accordance with the present invention.
  • the engine has, at least two, located in the upstream part of the turbine step 7.8, while the first turbine step 7 has the main gun 9.
  • Part II is ⁇ chni ⁇ nag ⁇ e ⁇ g ⁇ ⁇ ab ⁇ cheg ⁇ ⁇ ela, vy ⁇ l- cepts form ⁇ ame ⁇ y sg ⁇ aniya on v ⁇ de ⁇ y ⁇ azme- Shchen ⁇ m ⁇ ess ⁇ 12 ⁇ dachi ⁇ isli ⁇ elya, na ⁇ ime ⁇ , v ⁇ z- du ⁇ a, ne ⁇ b ⁇ dim ⁇ for sg ⁇ aniya ⁇ liva, ⁇ davaem ⁇ g ⁇ ⁇ is ⁇ chni ⁇ u II with ⁇ m ⁇ schyu ⁇ sun ⁇ i 13.
  • the main part of the power supply is provided with a free ring channel 19; - II - a corner> to a diametrical surface of 0-0 section of a koltsy channel of 19 (fig. ⁇ ). .3).
  • This camera is
  • the first step of the 7th turbine does not have a simple device, as its function is carried out by the electric pump 14.
  • the proposed gas turbine engine (Fig. 2) operates the following way.
  • heated working fluid mixed with coolant is not intended to be acceptable (not applicable).
  • P ⁇ myshlennaya ⁇ imenim ⁇ s ⁇ Iz ⁇ b ⁇ e ⁇ enie m ⁇ zhe ⁇ by ⁇ is ⁇ lz ⁇ van ⁇ in gaz ⁇ u ⁇ binny ⁇ dviga ⁇ elya ⁇ , ⁇ ednaznachenny ⁇ ddya ⁇ imeneniya ⁇ s ⁇ atsi ⁇ na ⁇ - 5 ny ⁇ ene ⁇ ge ⁇ iches ⁇ i ⁇ us ⁇ an ⁇ v ⁇ a ⁇ and sil ⁇ vy ⁇ us ⁇ an ⁇ v ⁇ a ⁇ , is ⁇ lzuemy ⁇ on ⁇ azlichny ⁇ occidentalemny ⁇ ⁇ ans ⁇ ny ⁇ s ⁇ eds ⁇ a ⁇ and v ⁇ zdushny ⁇ and v ⁇ dny ⁇ suda ⁇ .

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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)

Abstract

Le procédé consiste, dans une première étape, à modifier l'état thermodynamique d'un milieu de travail introduit dans au moins le premier étage de la turbine, étape pendant laquelle le milieu de travail introduit au moins dans le premier étage de la turbine est, avant son introduction, dilaté et soumis à une torsion par rapport à l'axe longitudinal du moteur à turbine à gas, après quoi le milieu de travail à l'état thermodynamique modifié est refroidi par le milieu de travail du premier étage de la turbine. Le moteur à turbine à gas comporte au moins deux étages (7, 8) de turbine situé dans la partie de passage (10), ainsi qu'une source (11) de milieu de travail chauffé. Le moteur est doté d'un éjecteur (14) présentant deux admissions et une sortie. La première admission (15) de l'éjecteur est reliée à la source (11) du milieu de travail chauffé, la seconde admission (16) de l'éjecteur (14) est reliée à la sortie du premier étage (7) de la turbine, et la sortie (17) de l'éjecteur (14) est reliée à l'admission du premier étage (7) de la turbine.
PCT/SU1991/000198 1991-10-08 1991-10-08 Procede de conversion d'energie thermique en energie mecanique dans un moteur a turbine a gas, et moteur a turbine a gas Ceased WO1993007370A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/SU1991/000198 WO1993007370A1 (fr) 1991-10-08 1991-10-08 Procede de conversion d'energie thermique en energie mecanique dans un moteur a turbine a gas, et moteur a turbine a gas

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/SU1991/000198 WO1993007370A1 (fr) 1991-10-08 1991-10-08 Procede de conversion d'energie thermique en energie mecanique dans un moteur a turbine a gas, et moteur a turbine a gas

Publications (1)

Publication Number Publication Date
WO1993007370A1 true WO1993007370A1 (fr) 1993-04-15

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/SU1991/000198 Ceased WO1993007370A1 (fr) 1991-10-08 1991-10-08 Procede de conversion d'energie thermique en energie mecanique dans un moteur a turbine a gas, et moteur a turbine a gas

Country Status (1)

Country Link
WO (1) WO1993007370A1 (fr)

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB412970A (en) * 1933-01-06 1934-07-06 British Thomson Houston Co Ltd Improvements in and relating to gas turbine cycles with interstage reheating
US2303381A (en) * 1941-04-18 1942-12-01 Westinghouse Electric & Mfg Co Gas turbine power plant and method
DE2454167A1 (de) * 1974-11-15 1976-05-20 Motoren Turbinen Union Verfahren zum starten einer brennkammer
SU922304A1 (ru) * 1980-09-22 1982-04-23 Всесоюзный Научно-Исследовательский Институт Природных Газов "Вниигаз" Газотурбинный агрегат
FR2552163A1 (fr) * 1983-09-21 1985-03-22 Onera (Off Nat Aerospatiale) Perfectionnements apportes aux installations a turbines a gaz dans lesquelles l'air issu de compresseur est rechauffe

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB412970A (en) * 1933-01-06 1934-07-06 British Thomson Houston Co Ltd Improvements in and relating to gas turbine cycles with interstage reheating
US2303381A (en) * 1941-04-18 1942-12-01 Westinghouse Electric & Mfg Co Gas turbine power plant and method
DE2454167A1 (de) * 1974-11-15 1976-05-20 Motoren Turbinen Union Verfahren zum starten einer brennkammer
SU922304A1 (ru) * 1980-09-22 1982-04-23 Всесоюзный Научно-Исследовательский Институт Природных Газов "Вниигаз" Газотурбинный агрегат
FR2552163A1 (fr) * 1983-09-21 1985-03-22 Onera (Off Nat Aerospatiale) Perfectionnements apportes aux installations a turbines a gaz dans lesquelles l'air issu de compresseur est rechauffe

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
Osnovy Teorii i Rascheta Zhidkostnykh Raketnykh Dvigatelei, Pod Redaktsiei B.M. KUDRYAVTSEVA, 1975, Vysshaya Shkola, (Moscow). *

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