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WO2000046488A2 - Turbine engine - Google Patents

Turbine engine Download PDF

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Publication number
WO2000046488A2
WO2000046488A2 PCT/GB2000/000310 GB0000310W WO0046488A2 WO 2000046488 A2 WO2000046488 A2 WO 2000046488A2 GB 0000310 W GB0000310 W GB 0000310W WO 0046488 A2 WO0046488 A2 WO 0046488A2
Authority
WO
WIPO (PCT)
Prior art keywords
turbine
engine
fuel
compressor
rotor
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/GB2000/000310
Other languages
French (fr)
Other versions
WO2000046488A3 (en
Inventor
Clive Maxwell Coote
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.)
Ripmax PLC
Original Assignee
Ripmax PLC
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 Ripmax PLC filed Critical Ripmax PLC
Priority to AU23067/00A priority Critical patent/AU2306700A/en
Publication of WO2000046488A2 publication Critical patent/WO2000046488A2/en
Anticipated expiration legal-status Critical
Publication of WO2000046488A3 publication Critical patent/WO2000046488A3/en
Ceased legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/52—Toroidal combustion chambers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/16—Aircraft characterised by the type or position of power plants of jet type
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F1/00—Ground or aircraft-carrier-deck installations
    • B64F1/34—Ground or aircraft-carrier-deck installations for starting propulsion plant
    • 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
    • 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
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22—Fuel supply 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
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/26—Starting; Ignition
    • F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
    • F02C7/275—Mechanical drives
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2203/00—Flying model aircraft, flying toy aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/08—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/70—Application in combination with
    • F05D2220/76—Application in combination with an electrical generator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/80—Size or power range of the machines
    • F05D2250/82—Micromachines

Definitions

  • Jet turbine engines used by aeromodellers suffer a number of inconveniences They must be run up initially using compressed air to rotate the turbine
  • the injectors must be preheated usually by propane
  • the fuel is supplied by an electric fuel pump which requires the aircraft to carry a speed controller and battery to control engine speed
  • Some conventional engines require oil to be mixed with the fuel so that when the engine is shut down, and still very hot, there is no lubrication
  • Others carry a separate oil supply with its inherent penalties of weight and complexity
  • a turbine engine having a compressor towards the front and a turbine towards the rear and connected by a shaft, an electric motor and/or generator having a rotor mounted on the shaft preferably between the compressor and the turbine
  • a small starter battery is suitable to run up a model engine and, with any necessary controller, is convenient to carry or may be mounted on board, if desired Once the engine is running, the starter battery and/or the receiver battery may be charged from the generator
  • the combustion chamber is preferably located behind the turbine, a first passage connecting an outlet of the compressor to an inlet of the combustion chamber, and a second passage connecting the outlet of the combustion chamber to an inlet of the turbine
  • the electric motor and/or generator preferably has a static armature
  • the rotor comprises at least one permanent magnet, which may be mounted on an impeller of the compressor
  • the rotor is in the form of a disc mounted directly on the shaft
  • the disc may be a conducting metal, e g copper, so that the motor and/or generator is in the form of an induction motor and/or generator
  • a turbine engine having a compressor towards the front, a turbine towards the rear and connected to the compressor by a shaft, and a fuel pump having a rotor mounted on the shaft for rotation therewith
  • the speed of the engine can be controlled by a valve and a servo
  • the servo can be powered by the aircraft's receiver battery
  • the rotor preferably has a central inlet and radially extending passages, the rotor being contained by a casing providing a fuel outlet
  • the fuel outlet is preferably connected via a fuel delivery passage to one or more injectors directed into the combustion chamber, a bypass valve also being connected to the fuel delivery passage to control flow rate of fuel delivered to the ⁇ njector(s)
  • the fuel pump also delivers fuel via a regulator valve to cool one or more bearings on which the shaft is mounted
  • a turbine engine having a compressor towards the front and a turbine towards the rear and connected by a shaft, the compressor and the turbine being connected by a combustion chamber into which fuel is injected and burnt, at least one injector for injecting fuel into the combustion chamber, which injector has a helical passage to impart vortex motion to fuel injected into the chamber
  • the vortex motion facilitates the injected fuel dividing sufficiently finely, e g to a vapour, that ignition can be obtained without preheating
  • Figure 1 is a longitudinal cross section through a micro jet turbine engine having a fuel pump embodying an aspect of the invention
  • Figure 2 is an enlarged cross section of the fuel pump
  • Figure 3 is a transverse cross section of the fuel pump
  • Figure 4 is a longitudinal cross section of part of a jet turbine engine having an alternative fuel pump embodying an aspect of the invention, and an electric starter motor and/or generator embodying another aspect of the invention
  • Figure 5 is a sectional detail showing an alternative electric starter motor and/or generator
  • FIG. 6 is a sectional detail showing another alternative starter motor and/or generator
  • Figure 7 is a detail of an injector of the engine of Figure 1
  • Figure 8 is a schematic diagram of the fuel system
  • the jet turbine engine 1 has a compressor 2 and a turbine 4 both mounted on and for rotation with a hollow shaft 6
  • the shaft 6 is mounted for rotation in bearings 8 contained by a casing 10
  • the casing 10 is mounted on a compressor diffuser 12 by a plate 14 and spacers 16
  • An external case 18 is connected to the diffuser 12 and defines a passage from an annular outlet 20 of the compressor to a toroidal combustion chamber 22 walls 24 of which are perforated to allow air from the compressor to enter
  • Fuel is injected into the combustion chamber 22 by a plurality of injectors 26, which extend through the casing 18, and ignited initially by a spark plug 28 Only one of the injectors is shown in the drawings
  • Exhaust gasses from the combustion chamber enter an annular inlet 30 of the turbine 4 and leave via an exhaust 32 which passes through a rear plate 34 of the casing
  • a rotor 36 of a fuel pump 37 is mounted on the shaft 6 for rotation therewith
  • the pump has a stator 38 within which the stator 38
  • the pump inlet 40 is connected to a fuel tank 56 via a filter 58
  • the outlet 54 is connected via a filter 60 to the injeGtors 26
  • a bypass valve 61 The valve is controlled by an electrical servo 64 such as is common in radio controlled models
  • the motor and/or generator illustrated in Figure 4 has a rotor 70 mounted on and for rotation with the shaft 6
  • the rotor carries a set of permanent magnets 72 disposed therearound, only two can be seen in Figure 4
  • a set of printed coils 74 is mounted on a stator 76 disposed in the casing 10
  • the coil extends into an air gap 78 in the rotor so that a magnetic circuit including the permanent magnets passes through the coils
  • a controller not shown, supplies AC or electrical pulses to cause the rotor to rotate in synchronism
  • the permanent magnets 72 are carried directly by the compressor rotor 2
  • the stator 76 carrying the coils 74 is mounted outside the casing 10
  • the motor and/or generator is an induction type A conducting (e g copper) disc 80 is mounted on. and for rotation with the shaft 6
  • the disc extends into an air gap 82 in a laminated core 84 on which windings 74 are located
  • An injector 26 is illustrated in Figure 7
  • the injector has a body 86
  • Fuel delivered from the fuel pump 37 passes through a passage 88 to a nozzle 90 which is threadedly mounted on the body
  • the fuel leaves the nozzle under pressure via a jet orifice 92
  • a section 94 of the passage 88 approaching the orifice 92 is conical and forms a seat for a conical surface 96 of a plug 98 which is urged into sealing engagement with the conical section by a compression spring 100
  • Spiral grooves 102 in the conical surface 96 of the plug provide spiral passages through which the fuel passes to give a vortex motion to the fuel injected through the orifice 92

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Supercharger (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Jet turbine engines used by aeromodellers suffer a number of incoveniences. They must be run up initially using compressed air to rotate the turbine. A turbine engine (1), is disclosed having a compressor (2) towards the front and a turbine (4) towards the rear and connected by a shaft (6). An electric motor (70) and/or generator has a rotor (72) mounted on the shaft preferably between the compressor and the turbine. This arrangement removes the need for a compressed air supply. A small starter battery is suitable to run up a model engine and, with any necessary controller, is convenient to carry or may be mounted on board, if desired. Once the engine is running, the starter battery and/or the receiver battery may be charged from the generator.

Description

TURBINE ENGINE This invention relates to turbine engines The background to the invention will be explained in relation to small jet turbine engines intended for model aircraft
Jet turbine engines used by aeromodellers suffer a number of inconveniences They must be run up initially using compressed air to rotate the turbine The injectors must be preheated usually by propane The fuel is supplied by an electric fuel pump which requires the aircraft to carry a speed controller and battery to control engine speed Some conventional engines require oil to be mixed with the fuel so that when the engine is shut down, and still very hot, there is no lubrication Others carry a separate oil supply with its inherent penalties of weight and complexity
Different aspects of the invention address respective ones of these inconveniences
In accordance with one aspect of the invention, there is provided a turbine engine, having a compressor towards the front and a turbine towards the rear and connected by a shaft, an electric motor and/or generator having a rotor mounted on the shaft preferably between the compressor and the turbine This arrangement removes the need for a compressed air supply A small starter battery is suitable to run up a model engine and, with any necessary controller, is convenient to carry or may be mounted on board, if desired Once the engine is running, the starter battery and/or the receiver battery may be charged from the generator
In order to keep the area in which the electric motor and/or generator is mounted between the compressor and the turbine relatively cool, the combustion chamber is preferably located behind the turbine, a first passage connecting an outlet of the compressor to an inlet of the combustion chamber, and a second passage connecting the outlet of the combustion chamber to an inlet of the turbine
The armature may rotate However, in order to simplify the construction, the electric motor and/or generator preferably has a static armature In one form, the rotor comprises at least one permanent magnet, which may be mounted on an impeller of the compressor
In an alternative, the rotor is in the form of a disc mounted directly on the shaft The disc may be a conducting metal, e g copper, so that the motor and/or generator is in the form of an induction motor and/or generator
In accordance with another aspect of the invention there is provided a turbine engine, having a compressor towards the front, a turbine towards the rear and connected to the compressor by a shaft, and a fuel pump having a rotor mounted on the shaft for rotation therewith This arrangement removes the need for a battery and speed controller to be carried by the aircraft The speed of the engine can be controlled by a valve and a servo The servo can be powered by the aircraft's receiver battery
The rotor preferably has a central inlet and radially extending passages, the rotor being contained by a casing providing a fuel outlet
The fuel outlet is preferably connected via a fuel delivery passage to one or more injectors directed into the combustion chamber, a bypass valve also being connected to the fuel delivery passage to control flow rate of fuel delivered to the ιnjector(s)
Preferably, the fuel pump also delivers fuel via a regulator valve to cool one or more bearings on which the shaft is mounted In accordance with another aspect of the invention, there is provided a turbine engine, having a compressor towards the front and a turbine towards the rear and connected by a shaft, the compressor and the turbine being connected by a combustion chamber into which fuel is injected and burnt, at least one injector for injecting fuel into the combustion chamber, which injector has a helical passage to impart vortex motion to fuel injected into the chamber The vortex motion facilitates the injected fuel dividing sufficiently finely, e g to a vapour, that ignition can be obtained without preheating Embodiments of the invention will now be described, by way of example, with reference to the accompanying drawings, in which
Figure 1 is a longitudinal cross section through a micro jet turbine engine having a fuel pump embodying an aspect of the invention, Figure 2 is an enlarged cross section of the fuel pump,
Figure 3 is a transverse cross section of the fuel pump, Figure 4 is a longitudinal cross section of part of a jet turbine engine having an alternative fuel pump embodying an aspect of the invention, and an electric starter motor and/or generator embodying another aspect of the invention, Figure 5 is a sectional detail showing an alternative electric starter motor and/or generator,
Figure 6 is a sectional detail showing another alternative starter motor and/or generator,
Figure 7 is a detail of an injector of the engine of Figure 1 , and Figure 8 is a schematic diagram of the fuel system
Referring to the drawings, the jet turbine engine 1 has a compressor 2 and a turbine 4 both mounted on and for rotation with a hollow shaft 6 The shaft 6 is mounted for rotation in bearings 8 contained by a casing 10 The casing 10 is mounted on a compressor diffuser 12 by a plate 14 and spacers 16 An external case 18 is connected to the diffuser 12 and defines a passage from an annular outlet 20 of the compressor to a toroidal combustion chamber 22 walls 24 of which are perforated to allow air from the compressor to enter Fuel is injected into the combustion chamber 22 by a plurality of injectors 26, which extend through the casing 18, and ignited initially by a spark plug 28 Only one of the injectors is shown in the drawings Exhaust gasses from the combustion chamber enter an annular inlet 30 of the turbine 4 and leave via an exhaust 32 which passes through a rear plate 34 of the casing In order to supply fuel to the injectors 26, a rotor 36 of a fuel pump 37 is mounted on the shaft 6 for rotation therewith The pump has a stator 38 within which the rotor rotates A fuel inlet 40 through the casing 10 communicates through the stator with a central toroidal chamber 42 in the stator The chamber 42 communicates with a central toroidal chamber 44 in the rotor 36 An annular surface 46 of the rotor is in sealing engagement with an annular surface 48 of the stator A plurality of backwardly curved radially extending grooves 50 in the annular surface 46 provide radially extending passages through which fuel is urged by centripetal force into a toroidal outlet chamber 52 thence to an outlet 54 An alternative arrangement is shown in Figure 4 mounted in front of the compressor In this case the radially extending passages are provided by radial bores 56 in the rotor
Referring to Figure 8, the pump inlet 40 is connected to a fuel tank 56 via a filter 58 The outlet 54 is connected via a filter 60 to the injeGtors 26 In order to control the flow to the injectors, a bypass valve 61 The valve is controlled by an electrical servo 64 such as is common in radio controlled models
In order to cool the bearings 8, especially the rear most since that is closest the hot exhaust, a small amount of fuel is supplied to them via pipes 66 in Figure 4, and via a flow regulator valve 66 and a filter 68 shown in Figure 8 In the arrangement shown in Figure 5, a single pipe 66 is used to inject fuel between the bearings Fuel injected into the bearings finds its way to the compressor outlet or to the turbine inlet along paths indicated by arrows in Figures 4 and 5 As may be seen, the path from the rear bearing passes behind the turbine which is cooled thereby In figure 4, the hotter rear bearing abuts a heat conducting disc or cylinder 67, which is mounted on the shaft and which acts as a heat sink The cylinder is formed with a helical groove 69 in its periphery This acts to draw fuel through the bearing and thus to cool itself and also the bearing directly In the detailed part sections shown in Figures 4, 5 and 6, an electric starter motor and/or generator 70 is illustrated
The motor and/or generator illustrated in Figure 4 has a rotor 70 mounted on and for rotation with the shaft 6 The rotor carries a set of permanent magnets 72 disposed therearound, only two can be seen in Figure 4 A set of printed coils 74 is mounted on a stator 76 disposed in the casing 10 The coil extends into an air gap 78 in the rotor so that a magnetic circuit including the permanent magnets passes through the coils As a motor, a controller, not shown, supplies AC or electrical pulses to cause the rotor to rotate in synchronism In the engine illustrated in Figure 5, the permanent magnets 72 are carried directly by the compressor rotor 2 The stator 76 carrying the coils 74, is mounted outside the casing 10
In the engine illustrated in Figure 6, the motor and/or generator is an induction type A conducting (e g copper) disc 80 is mounted on. and for rotation with the shaft 6 The disc extends into an air gap 82 in a laminated core 84 on which windings 74 are located
An injector 26 is illustrated in Figure 7 The injector has a body 86 Fuel delivered from the fuel pump 37 passes through a passage 88 to a nozzle 90 which is threadedly mounted on the body The fuel leaves the nozzle under pressure via a jet orifice 92 A section 94 of the passage 88 approaching the orifice 92 is conical and forms a seat for a conical surface 96 of a plug 98 which is urged into sealing engagement with the conical section by a compression spring 100 Spiral grooves 102 in the conical surface 96 of the plug provide spiral passages through which the fuel passes to give a vortex motion to the fuel injected through the orifice 92

Claims

1 A turbine engine having a compressor towards the front and a turbine towards the rear and connected by a shaft, an electric motor and/or generator/and or generator having a rotor mounted on the shaft 2 A turbine as claimed in claim 1 , wherein the rotor is mounted between the compressor and the turbine
3 An engine as claimed in claim 1 or 2, having a combustion chamber located behind the turbine, a first passage connecting an outlet of the compressor to an inlet of the combustion chamber, and a second passage connecting the outlet of the combustion chamber to an inlet of the turbine
4 An engine as claimed in any preceding claim, wherein the electric motor and/or generator and/or generator has a static armature
5 An engine as claimed in claim 4, wherein the rotor comprises at least one permanent magnet 6 An engine as claimed in claim 5, wherein the compressor has an impeller on which the magnet(s) is or are mounted
7 An engine as claimed in claim 4, wherein the rotor is in the form of a disc mounted directly on the shaft
8 An engine as claimed in claim 7, wherein the motor and/or generator is an induction motor and/or generator
9 A turbine engine, having a compressor towards the front, a turbine towards the rear and connected to the compressor by a shaft, and a fuel pump having a rotor mounted on the shaft for rotation therewith
10 An engine as claimed in claim 9, wherein the rotor has a central inlet and radially extending passages, the rotor being contained by a casing providing a fuel outlet 1 1 An engine as claimed in claim 9 or 10, wherein the fuel outlet is connected via a fuel delivery passage to one or more injectors directed into the combustion chamber, a bypass valve also being connected to the fuel delivery passage to control flow rate of fuel delivered to the ιnjector(s) 12 An engine as claimed in claim 10 or 1 1 , wherein the fuel pump also delivers fuel via a regulator valve to cool one or more bearings on which the shaft is mounted
13 A turbine engine, having a compressor towards the front and a turbine towards the rear and connected by a shaft, the compressor and the turbine being connected by a combustion chamber into which fuel is injected and burnt, at least one injector for injecting fuel into the combustion chamber, which injector has at least one outlet passage directed to impart vortex motion to fuel injected into the chamber
14 A turbine as claimed in claim 13, wherein the outlet passage(s) is/are spiral
PCT/GB2000/000310 1999-02-04 2000-02-02 Turbine engine Ceased WO2000046488A2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AU23067/00A AU2306700A (en) 1999-02-04 2000-02-02 Turbine engine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GBGB9902502.5A GB9902502D0 (en) 1999-02-04 1999-02-04 Turbine engine
GB9902502.5 1999-02-04

Publications (2)

Publication Number Publication Date
WO2000046488A2 true WO2000046488A2 (en) 2000-08-10
WO2000046488A3 WO2000046488A3 (en) 2003-05-08

Family

ID=10847118

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/GB2000/000310 Ceased WO2000046488A2 (en) 1999-02-04 2000-02-02 Turbine engine

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AU (1) AU2306700A (en)
GB (1) GB9902502D0 (en)
WO (1) WO2000046488A2 (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008055397A1 (en) * 2006-11-07 2008-05-15 Beijing Afillip Air Suspension Train Technology Institute Electric aero compressor
FR2983248A1 (en) * 2011-11-29 2013-05-31 Turbomeca TURBOMACHINE COMPRISING AN ELECTRIC-ACTIVATED FUEL SUPPLY PUMP AND FUEL SUPPLY METHOD OF A TURBOMACHINE
CN118669236A (en) * 2024-08-01 2024-09-20 清华大学 Detonation engine and aircraft

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Publication number Priority date Publication date Assignee Title
US3932988A (en) * 1972-10-25 1976-01-20 Beaufrere Albert H Fuel slinger combustor
EP0263110B1 (en) * 1985-06-29 1989-10-04 GRIEPENTROG, Hartmut Machine with magnetic bearing rotor and electric radial field machine
US5042256A (en) * 1986-07-28 1991-08-27 Teledyne Industries, Inc. Turbine shaft fuel pump
US4769996A (en) * 1987-01-27 1988-09-13 Teledyne Industries, Inc. Fuel transfer system for multiple concentric shaft gas turbine engines
JPH03115739A (en) * 1989-09-28 1991-05-16 Isuzu Motors Ltd Turbocharger with rotary electric machine
US5819524A (en) * 1996-10-16 1998-10-13 Capstone Turbine Corporation Gaseous fuel compression and control system and method

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008055397A1 (en) * 2006-11-07 2008-05-15 Beijing Afillip Air Suspension Train Technology Institute Electric aero compressor
FR2983248A1 (en) * 2011-11-29 2013-05-31 Turbomeca TURBOMACHINE COMPRISING AN ELECTRIC-ACTIVATED FUEL SUPPLY PUMP AND FUEL SUPPLY METHOD OF A TURBOMACHINE
WO2013098498A1 (en) * 2011-11-29 2013-07-04 Turbomeca Turbine engine comprising an electrically activated fuel supply pump, and turbine engine fuel supply method
CN103946484A (en) * 2011-11-29 2014-07-23 涡轮梅坎公司 Turbine engine and method of fueling a turbine engine including an electrically activated fuel supply pump
JP2015503052A (en) * 2011-11-29 2015-01-29 ターボメカＴｕｒｂｏｍｅｃａ Turbine engine provided with electric fuel supply pump, and fuel supply method for turbine engine
CN103946484B (en) * 2011-11-29 2015-11-25 涡轮梅坎公司 Turbine engine and method of fueling a turbine engine including an electrically activated fuel supply pump
US9546599B2 (en) 2011-11-29 2017-01-17 Turbomeca Turbine engine comprising an electrically activated fuel supply pump, and turbine engine fuel supply method
RU2610360C2 (en) * 2011-11-29 2017-02-09 Турбомека Turbo-machine containing fuel supply pump with electric drive and method of turbo-machine fuel supply
CN118669236A (en) * 2024-08-01 2024-09-20 清华大学 Detonation engine and aircraft
CN118669236B (en) * 2024-08-01 2024-12-03 清华大学 Detonation engine and aircraft

Also Published As

Publication number Publication date
GB9902502D0 (en) 1999-03-24
WO2000046488A3 (en) 2003-05-08
AU2306700A (en) 2000-08-25

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