WO1998012427A1 - Turbine a gaz a commande electrique fonctionnant en discontinu - Google Patents

Turbine a gaz a commande electrique fonctionnant en discontinu Download PDF

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Publication number
WO1998012427A1
WO1998012427A1 PCT/HU1997/000054 HU9700054W WO9812427A1 WO 1998012427 A1 WO1998012427 A1 WO 1998012427A1 HU 9700054 W HU9700054 W HU 9700054W WO 9812427 A1 WO9812427 A1 WO 9812427A1
Authority
WO
WIPO (PCT)
Prior art keywords
air
cylinders
cylinder
gas turbine
control
Prior art date
Application number
PCT/HU1997/000054
Other languages
German (de)
English (en)
Inventor
Piroska KUHN
Original Assignee
Diviak Janos
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 Diviak Janos filed Critical Diviak Janos
Priority to AU47184/97A priority Critical patent/AU4718497A/en
Publication of WO1998012427A1 publication Critical patent/WO1998012427A1/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
    • F02C5/00—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion
    • 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
    • F02C5/00—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion
    • F02C5/12—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion the combustion chambers having inlet or outlet valves, e.g. Holzwarth gas-turbine plants

Definitions

  • the invention relates to a discontinuously operating gas turbine with electrical control, the gas turbine directly converting the thermal energy released during combustion into kinetic energy and, in contrast to the conventional mechanical controls, being electrically controlled.
  • a fundamental disadvantage of piston engines results from the functional principle and occurs in both the Otto and the Diesel systems.
  • the thermal energy generated in the cylinder of the internal combustion engine during the combustion of the fuel generates an increase in pressure and the crank drive converts this into mechanical work.
  • this work is only done in the periodically repeating expansion cycle because the intake, compression and exhaust cycles only take up work and do not do any mechanical work.
  • Another disadvantage is that the piston in the cylinder performs a linear movement in an alternating direction, so it must stop at the top and bottom dead center in order to start a movement in the opposite direction. During this time, the piston moves at changing speeds because it has to accelerate and slow down alternately during the movement.
  • crank drive which converts the linear movement of the piston into rotary motion.
  • the unit which consists of several constructions, consumes a large amount of friction and also significantly increases the weight of the engine.
  • Another problem is that not all crank drive units make a rotary motion.
  • the discontinuously operating gas turbine requires a compressor with low output because, on the one hand, the compression ratio can be low, since the pressure rise occurs during the combustion process and, on the other hand, the excess air and thus the required total air volume can also be less, since the turbine operates discontinuously. Because of the latter, the average temperature of the construction elements is much lower than the highest gas temperature, similar to the piston engines that work with alternating motion. Your control is mechanical.
  • the air consumption of the gas turbines is several times that of the piston engines with the same output. Accordingly, the amount of exhaust gas from the gas turbines is larger than that of the internal combustion engines.
  • Heat exchangers are used to reduce fuel consumption and increase efficiency. These are heavy, large-volume facilities.
  • the invention is based on the knowledge that the major part of these disadvantages does not occur in the discontinuously operating gas turbines, while at the same time, due to the completely different functional principle, the fundamental disadvantages of the piston engines resulting from their construction (four-stroke, large friction losses, positive connection between the rotary movement of the engine and the control of the cylinders) can be canceled.
  • the object to be achieved by the invention is to create such a discontinuously operating gas turbine, which switches off the mechanical control which consumes high friction energy, eliminates its positive connection with the rotational speed and sets the optimum time required for the individual work cycles enables, furthermore makes the starter motor and idling superfluous and only maintains their function when the accelerator pedal is depressed and at the same time continues the control of their cylinders when restarting from the set state.
  • the solution to the problem was assumed to be a discontinuously operating gas turbine, which is provided with a fuel source, an air supply and fuel-air mixture-burning cylinders, the inlet and outlet openings of the cylinders being assigned control elements and from which gases are generated at high speed are guided into the housing of a double-shaft turbine, a working turbine driving a transmission gear and a compressor turbine driving a centrifugal compressor being arranged in the housing mentioned, the air outlet of the centrifugal compressor being connected to a mixing tube which delivers fuel to the air mixture and
  • the object was achieved in such a way that the cylinders form at least one pair of cylinders and a pneumatic control cylinder is connected to the cylinder opening of the individual cylinders, in which the control element is an electrical one it is arranged air valve actuated control piston performing the closing and opening of the cylinders, the actuating circuits of the air valves and the ignition circuits of the cylinders being controlled or regulated by an electrical control system which contains the coordinated function of
  • the electrical control of the discontinuously operating gas turbine designed according to the invention consumes far less energy compared to the mechanical control, no starter motor is required to start it, but it can be started and stopped simply by depressing or releasing the accelerator pedal and only works as long as the accelerator pedal is held down.
  • the control process is interrupted, which means that, unlike the piston engines, the gas turbine does not idle, with which significant fuel savings and environmental protection can be achieved.
  • the optimum value of the time required for the individual work facts (charging, explosion, exhaust) can be set.
  • the electrical control system of the discontinuously operating gas turbine according to the invention preferably contains the respective functional state of the individual cylinders in the event of an interruption of the function and retaining circuits which activate the interrupted state when restarted.
  • the air supply source of the control piston actuated by the electrical air valves is formed by at least one air container, which is optionally connected to the outlet of the centrifugal compressor via a further air container and via mechanical valves and at the same time via an electrical one Air valve opens into the mixing tube, thus the compressed air required to start the turbine and to operate the control piston is secured regardless of the respective output of the centrifugal compressor.
  • a servo compressor is connected to the at least one air container which forms the air supply source for the control pistons actuated by the electrical air valves via a pressure switch. This solution also secures the compressed air which has the required pressure when the supply of the air containers is no longer sufficient for this.
  • the electrical control system prefferably keeps the electrical air valve, which is arranged between the air container and the mixing tube, open when the accelerator pedal is fully depressed. contains the switch.
  • FIG. 1 schematically shows the basic structure of a gas turbine according to the invention
  • FIG. 2 shows the circuit diagram of the electrical control system of the gas turbine according to FIG. 1.
  • the function of the gas turbine according to the invention is ensured by pairs of cylinders. While one cylinder is being charged, the other cylinder is working.
  • the cylinder pairs are provided with a control which is delayed relative to one another.
  • the associated cylinder pairs are as follows:
  • the relay V1, V2, V3, V4 picks up via the microswitch G1.
  • Relay V4 is switched on by the contact of relay V2.
  • the control is operated with the accelerator pedal. In the basic position, the accelerator pedal holds the switch G1 in the depressed state and the switch G1 is in the position shown in the figure. Even a slight depression of the accelerator pedal switches switch G1 and relay V1, V2, V3 drops out (switches off). Relay V4 drops out later because it is delayed by a capacitor.
  • the relay V5 picks up via the switch G1, while the contact of the relay V4 switches on the electric air valve Szl.
  • the compressed air flows into the mixing tube 10 via the air valve Szl, with this air being mixed with fuel after the wing valve 11 actuated by the accelerator pedal.
  • the fuel is supplied from the fuel tank 19 via the carburetor 20.
  • Compressed air flows from the air container 14 via the air valves Sz1, Sz2, Sz3, Sz4 into the control cylinders 17.
  • the control pistons 21 of the cylinders H1, H2, H3, H4 move to the right, while the control pistons 21 of the cylinders H5, H6, Move H7, H8 to the left.
  • Fuel mixture flows from the mixing tube 10 via the control pistons 21 into the cylinders H1, H2, H3, H4, while after combustion of the fuel from the cylinders H5, H6, H7, H8, the gas flowing out at high speed escapes via the control pistons 21 and the compressor turbine 22 and the power turbine 25 set in rotation.
  • the useful work is done by the transmission gear 30.
  • the centrifugal compressor 26 feeds air into the mixing tube 10 via the valve 27.
  • the relay V4 is only in the tightened state for the time of starting, it then drops out and also switches off the electric air valve Szl. The air required for further function is thus supplied by the centrifugal compressor 26.
  • relay K1 drops out
  • the circuit of relay E1 is also interrupted.
  • the dropout of the relay E1 is also delayed by a capacitor, so the dropout of the relay only takes place after the cylinders H1 and H5 have been safely locked.
  • the circuit of the primary coil of the ignition transformer T1 is interrupted and arises as a result of the self-induction high voltage which arises in the secondary coil Between the electrodes of the spark plug 35 of the cylinder H1, a spark ignites the mixture in the cylinder.
  • relay E1 drops out
  • relay E5 also picks up, then air valve Sz5 and relay E5 switch on.
  • the air valve Sz5 actuates the control pistons 21 of the cylinders H1 and H5.
  • the control piston of the cylinder H1 moves to the left, while the control piston of the cylinder H5 moves to the right.
  • the cylinder H1 is exhausted and the cylinder H5 is charged.
  • relay E1 When switched off, relay E1 also interrupts the circuit of relay K2.
  • Relay K2 drops out after a delay.
  • the air valve Sz2 switches off and the control pistons 21 of the cylinders H2, H6 return to their basic position. Close cylinders H2 and H6. Charging is completed in cylinder H2, while exhausting is terminated in cylinder H6.
  • relay E2 After locking cylinders H2 and H6, relay E2 switches off, which opens the primary circuit of ignition transformer T2. The spark ignites the mixture in cylinder H2.
  • relay K6 also picks up, then air valve Sz6 and relay E6 switch on.
  • the air valve Sz6 actuates the control pistons 21 of the cylinders H2 and H6.
  • the cylinder H2 is exhausted and the cylinder H6 is charged.
  • the other cylinders are charged and muffled in a similar manner.
  • the state of charge of the cylinders is regulated with the aid of the wing valve 11 actuated by the accelerator pedal.
  • the microswitch G2 is switched on by fully depressing the accelerator pedal. This immediately switches the air valve Sz1 and then compressed air flows from the air container 9 into the mixing tube 10. This continues until the pressure of the air supplied by the compressor turbine 26 is balanced with the pressure of the air in the air container 9.
  • the air valve Sz1 remains open. If the accelerator pedal is completely released (released), the returned accelerator pedal actuates the microswitch G1. This switches the release V5 and relays V1, V2, V3, V4 on. The periodic repetition of the control is interrupted.
  • the circuit determines the holding circuit of the four relays K currently operating via the make contact of the relays V1, V2, V3.
  • the relays marked with K also keep four relays marked with E in the energized state.
  • the electric air valves switch off and the cylinders lock.
  • the primary circuit of the ignition transformer currently operating is closed via the resistor R, since the relay V5 has dropped out.
  • Resistor R performs two functions: on the one hand it does not allow one of the ignition transformers T1-T8 to deliver a spark when relay V5 drops out, and on the other hand it protects the ignition transformer against harmful overheating (for example in the event of a prolonged switch-on that is not suitable for operation) . If the accelerator pedal is depressed again, the control continues from where it was previously interrupted.
  • the compressed air reaches the air container 9 via the valve 32. Its pressure corresponds to the maximum pressure of the air supplied by the compressor turbine 26. Of course, the pressure can be increased if a servo compressor is used. In this case, the sudden acceleration of the turbine can be increased.
  • the air required to actuate the control pistons 21 comes from the container 9 via the valve 12 in the air container 14. In the case of a compressor turbine that secures a low pressure, its pressure is increased with the aid of the servo compressor 16.
  • the desired pressure can be set using the pressure switch 15.
  • the control of the gas turbine is instead of the mechanical control, which consumes a high amount of friction work, using an electrical control Control, which uses little energy, trained.
  • the solution according to the invention is environmentally friendly, since the gas turbine only works as long as the accelerator pedal is held in the depressed state, i.e. there is no idle.

Landscapes

  • 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)
  • Supercharger (AREA)

Abstract

La présente invention concerne une turbine à gaz fonctionnant en discontinu, comprenant une source de carburant et, assurant l'amenée d'air, au moins un réservoir d'air associé à des cylindres qui consument le mélange air/carburant sous l'action d'une étincelle d'allumage, dont les orifices d'admission et de sortie sont assujettis à des organes de commande et d'où des gaz sont acheminés à grande vitesse dans le boîtier d'une turbine à double ondulation dans lequel se trouve une turbine entraînant un multiplicateur et une turbine de compresseur entraînant un compresseur centrifuge dont la sortie d'air est associé à un tube mélangeur qui achemine aux cylindres le mélange air/carburant. Selon l'invention, les cylindres (H1-H8) forment au moins une paire (H1, H5;...), et un cylindre de commande à air comprimé (17) est raccordé à l'ouverture de chaque cylindre (H1-H8). Dans ce cylindre de commande à air comprimé est installé un piston pilote (21) qui officie comme organe de commande pour déclencher à l'aide d'un robinet d'air électrique (Sz1-Sz8) l'ouverture et la fermeture des cylindres (H1-H8), les circuits électriques moteurs de ce robinet d'air (Sz1-Sz8) et les circuits d'allumage des cylindres (H1-H8) étant commandés ou réglés par un système de commande électrique qui comprend des circuits (K1-K8; E1-E8) de délai pour assurer le fonctionnement synchronisé des cylindres. (Fig. 2)
PCT/HU1997/000054 1996-09-23 1997-09-23 Turbine a gaz a commande electrique fonctionnant en discontinu WO1998012427A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AU47184/97A AU4718497A (en) 1996-09-23 1997-09-23 Power-controlled gas turbine in intermittent operation

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
HUP9602589 1996-09-23
HU9602589A HUP9602589A3 (en) 1996-09-23 1996-09-23 Electrically controlled intermittent gas turbine

Publications (1)

Publication Number Publication Date
WO1998012427A1 true WO1998012427A1 (fr) 1998-03-26

Family

ID=89994296

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/HU1997/000054 WO1998012427A1 (fr) 1996-09-23 1997-09-23 Turbine a gaz a commande electrique fonctionnant en discontinu

Country Status (3)

Country Link
AU (1) AU4718497A (fr)
HU (1) HUP9602589A3 (fr)
WO (1) WO1998012427A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2829528A1 (fr) * 2001-09-07 2003-03-14 Bernard Gilbert Macarez Pulsomoteur-turbomoteur a impulsion-turbine a gaz a chambre de combustion impulsionnelle et a detente de bouffees

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB382497A (en) * 1932-02-10 1932-10-27 Arthur Stickland A gas driven turbine
DE606883C (de) * 1930-12-12 1934-12-12 Bbc Brown Boveri & Cie Verpuffungsturbine mit Beaufschlagung durch mehrere Gasstrahlen
CH176126A (de) * 1933-08-25 1935-03-31 Mark Brooke Francis Vorrichtung zur Erzeugung von Druckgasen zum Betrieb von Kraftmaschinen, insbesondere von Gasturbinen.
DE703195C (de) * 1938-04-30 1941-03-03 Oerlikon Maschf Waermekraftanlage
WO1980002444A1 (fr) * 1979-05-03 1980-11-13 Meur Henri Le Turbine a explosions et distributeurs de gaz
DE3511971A1 (de) * 1985-04-02 1986-10-02 Bernhard 4530 Ibbenbüren Veltmann Nutzung von explosivem staub organischer stoffe in energie
EP0372135A1 (fr) * 1987-02-24 1990-06-13 Ahmed Salem Moteur à combustion interne

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE606883C (de) * 1930-12-12 1934-12-12 Bbc Brown Boveri & Cie Verpuffungsturbine mit Beaufschlagung durch mehrere Gasstrahlen
GB382497A (en) * 1932-02-10 1932-10-27 Arthur Stickland A gas driven turbine
CH176126A (de) * 1933-08-25 1935-03-31 Mark Brooke Francis Vorrichtung zur Erzeugung von Druckgasen zum Betrieb von Kraftmaschinen, insbesondere von Gasturbinen.
DE703195C (de) * 1938-04-30 1941-03-03 Oerlikon Maschf Waermekraftanlage
WO1980002444A1 (fr) * 1979-05-03 1980-11-13 Meur Henri Le Turbine a explosions et distributeurs de gaz
DE3511971A1 (de) * 1985-04-02 1986-10-02 Bernhard 4530 Ibbenbüren Veltmann Nutzung von explosivem staub organischer stoffe in energie
EP0372135A1 (fr) * 1987-02-24 1990-06-13 Ahmed Salem Moteur à combustion interne

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
DATABASE WPI WORLD PATENT INF 1 January 1900 (1900-01-01), XP002054993, Database accession no. SU-184065 *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2829528A1 (fr) * 2001-09-07 2003-03-14 Bernard Gilbert Macarez Pulsomoteur-turbomoteur a impulsion-turbine a gaz a chambre de combustion impulsionnelle et a detente de bouffees
WO2003023206A1 (fr) * 2001-09-07 2003-03-20 Bernard Macarez Turbine a gaz avec combustion intermittente

Also Published As

Publication number Publication date
HU9602589D0 (en) 1996-11-28
HUP9602589A2 (hu) 1998-04-28
HUP9602589A3 (en) 1999-03-29
AU4718497A (en) 1998-04-14

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