WO1987006976A1 - Statoreacteur - Google Patents

Statoreacteur Download PDF

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Publication number
WO1987006976A1
WO1987006976A1 PCT/CH1987/000054 CH8700054W WO8706976A1 WO 1987006976 A1 WO1987006976 A1 WO 1987006976A1 CH 8700054 W CH8700054 W CH 8700054W WO 8706976 A1 WO8706976 A1 WO 8706976A1
Authority
WO
WIPO (PCT)
Prior art keywords
compression
chamber
air
drum
closed
Prior art date
Application number
PCT/CH1987/000054
Other languages
German (de)
English (en)
Inventor
Daniel Buchser
Original Assignee
Daniel Buchser
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 Daniel Buchser filed Critical Daniel Buchser
Publication of WO1987006976A1 publication Critical patent/WO1987006976A1/fr

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/02—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof the jet being intermittent, i.e. pulse-jet
    • F02K7/06—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof the jet being intermittent, i.e. pulse-jet with combustion chambers having valves

Definitions

  • the jet engines used today for aircraft are based on the principle that air is sucked in, compressed and pressed into a combustion chamber by means of a turbine, where the energy-generating combustion takes place with the addition of fuel, the hot gases of which in turn drive a turbine, which in turn drives a shaft with the first turbine is connected and thus drives it.
  • the main disadvantage of this system is that it only works efficiently in the subsonic area, since only subsonic air can be compressed using a turbine.
  • the incoming air must therefore first be braked, whereby it is already compressed as a result of the dynamic pressure that arises, so that superfluous compression performance is available or the engine works with poor efficiency due to the additional air resistance etc.
  • the simplest solution to the problem would be to compress the incoming air directly into the combustion chamber by means of a pitot tube, which would, however, cause the drive jet to kick back and the flow to break off or the thrust to collapse. For this reason, between the pitot tube, where the air is compressed, and the combustion chamber, where it is used for combustion, only one direction has to be inserted by means of a casual apparatus which conveys the compressed air into the combustion chamber.
  • the advantage of the present invention is, in particular, that as the speed increases as a result of the back pressure increasing in the square, the efficiency improves and the compression ratio can be increased practically as desired.
  • the whole system is technically relatively simple compared to a conventional turbine engine, especially since the drive of the compression drum can also be accomplished by means of attached turbine blade wheels and the air flow.
  • the components of the engine are shown on page 2 of the drawings, the dashed lines indicating the assembly.
  • the individual elements are the compression drum 1 mounted between the front 3 and the rear 4 cover with the compression chambers 2, into which the air penetrates and is compressed through the pitot tube 5 and the inlet opening 6.
  • the compression chamber becomes closed and transported to the outlet opening 8, through which the air flows into the combustion chamber 7, where it is used to burn the fuel supplied through the fuel line 9.
  • the compression chamber passes between the fresh air inlet opening 10 and outlet opening 11, where the compression chamber is flushed out with fresh air.
  • a three-phase ramjet engine is shown, ie an engine whose individual compression chambers carry out the three operations three times in succession with each revolution of the compression drum.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)

Abstract

Le statoréacteur consiste en un moteur à réaction pour vol à haute vitesse qui, au lieu des turbines en usage jusqu'à présent, techniquement exigentes et thermiquement sensibles, pour aspirer et comprimer l'air, utilise une prise d'air (5) du type Pitot par laquelle l'air entrant est freiné et du fait de sa vitesse propre relative et de la pression dynamique qui y règne est comprimé dans une chambre d'un tambour (2) fermée en aval par un couvercle (4). Cette chambre est également fermée du côté amont par un couvercle (3) par rotation du tambour (1) et est transportée en face d'une chambre de combustion (7) dans laquelle l'air comprimé peut s'échapper à travers une ouverture (8) du couvercle aval (4) et servir à la combustion. En poursuivant sa rotation, la chambre parvient finalement entre un orifice (10) d'admission d'air frais et un orifice (11) d'échappement, ce qui lui permet d'être purgée avec de l'air frais et préparée à recevoir de nouveau de l'air comprimé.
PCT/CH1987/000054 1986-05-14 1987-05-14 Statoreacteur WO1987006976A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH195486 1986-05-14
CH1954/86-1 1986-05-14

Publications (1)

Publication Number Publication Date
WO1987006976A1 true WO1987006976A1 (fr) 1987-11-19

Family

ID=4222471

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CH1987/000054 WO1987006976A1 (fr) 1986-05-14 1987-05-14 Statoreacteur

Country Status (2)

Country Link
AU (1) AU7351887A (fr)
WO (1) WO1987006976A1 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1138922A1 (fr) * 2000-03-31 2001-10-04 General Electric Company Moteur a turbine combiné avec un moteur a explosion par impulsion
US6666018B2 (en) 2000-03-31 2003-12-23 General Electric Company Combined cycle pulse detonation turbine engine
US6813878B2 (en) 2002-12-11 2004-11-09 General Electric Company Methods and apparatus for operating gas turbine engines
US6868665B2 (en) 2001-12-21 2005-03-22 General Electric Company Methods and apparatus for operating gas turbine engines
US6883302B2 (en) 2002-12-20 2005-04-26 General Electric Company Methods and apparatus for generating gas turbine engine thrust with a pulse detonation thrust augmenter
US6983586B2 (en) 2003-12-08 2006-01-10 General Electric Company Two-stage pulse detonation system

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR409068A (fr) *
DE692163C (de) * 1938-02-23 1940-06-13 Luigi Stipa Heizluftstrahltriebwerk
CH251279A (de) * 1945-12-29 1947-10-15 Bbc Brown Boveri & Cie Antriebsanlage an Flugzeugen.
US2515644A (en) * 1947-03-11 1950-07-18 Daniel And Florence Guggenheim Rotating valve for multiple resonance combustion chambers
US2930196A (en) * 1951-03-30 1960-03-29 Cornell Aeronautical Labor Inc Valved intermittent combustion reaction engine
US2942412A (en) * 1952-09-30 1960-06-28 Curtiss Wright Corp Pulse detonation jet propulsion
US3008292A (en) * 1961-02-15 1961-11-14 Jr Joseph G Logan Wave engines
US3328956A (en) * 1965-04-01 1967-07-04 Wilhelm Kusters Pulsating combustion process and burner apparatus

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR409068A (fr) *
DE692163C (de) * 1938-02-23 1940-06-13 Luigi Stipa Heizluftstrahltriebwerk
CH251279A (de) * 1945-12-29 1947-10-15 Bbc Brown Boveri & Cie Antriebsanlage an Flugzeugen.
US2515644A (en) * 1947-03-11 1950-07-18 Daniel And Florence Guggenheim Rotating valve for multiple resonance combustion chambers
US2930196A (en) * 1951-03-30 1960-03-29 Cornell Aeronautical Labor Inc Valved intermittent combustion reaction engine
US2942412A (en) * 1952-09-30 1960-06-28 Curtiss Wright Corp Pulse detonation jet propulsion
US3008292A (en) * 1961-02-15 1961-11-14 Jr Joseph G Logan Wave engines
US3328956A (en) * 1965-04-01 1967-07-04 Wilhelm Kusters Pulsating combustion process and burner apparatus

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1138922A1 (fr) * 2000-03-31 2001-10-04 General Electric Company Moteur a turbine combiné avec un moteur a explosion par impulsion
US6442930B1 (en) 2000-03-31 2002-09-03 General Electric Company Combined cycle pulse detonation turbine engine
US6666018B2 (en) 2000-03-31 2003-12-23 General Electric Company Combined cycle pulse detonation turbine engine
US6868665B2 (en) 2001-12-21 2005-03-22 General Electric Company Methods and apparatus for operating gas turbine engines
US6813878B2 (en) 2002-12-11 2004-11-09 General Electric Company Methods and apparatus for operating gas turbine engines
US6883302B2 (en) 2002-12-20 2005-04-26 General Electric Company Methods and apparatus for generating gas turbine engine thrust with a pulse detonation thrust augmenter
US6983586B2 (en) 2003-12-08 2006-01-10 General Electric Company Two-stage pulse detonation system

Also Published As

Publication number Publication date
AU7351887A (en) 1987-12-01

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