WO1996041940A1 - Jet supersonique a commande de la section critique - Google Patents

Jet supersonique a commande de la section critique Download PDF

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Publication number
WO1996041940A1
WO1996041940A1 PCT/CZ1996/000013 CZ9600013W WO9641940A1 WO 1996041940 A1 WO1996041940 A1 WO 1996041940A1 CZ 9600013 W CZ9600013 W CZ 9600013W WO 9641940 A1 WO9641940 A1 WO 9641940A1
Authority
WO
WIPO (PCT)
Prior art keywords
jet
section
supersonic jet
cross
supersonic
Prior art date
Application number
PCT/CZ1996/000013
Other languages
English (en)
Inventor
Bohumil Svoboda
Original Assignee
Bohumil Svoboda
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 Bohumil Svoboda filed Critical Bohumil Svoboda
Priority to AU58086/96A priority Critical patent/AU5808696A/en
Publication of WO1996041940A1 publication Critical patent/WO1996041940A1/fr

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
    • F02K9/86—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control using nozzle throats of adjustable cross- section
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/10—Varying effective area of jet pipe or nozzle by distorting the jet pipe or nozzle
    • 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
    • F05D2250/20—Three-dimensional
    • F05D2250/27—Three-dimensional hyperboloid

Definitions

  • the invention relates to a supersonic jet with a controllable critical cross section.
  • Laval jet To transform pressure power of gasses to kinetic one of a supersonic velocity, there is used "a Laval jet", the critical cross section of which cannot be altered. It is suitable to be used in cases where the pressure drop of gasses in front of the jet and behind it is constant. In case that the pressure drop is altered, the efficiency of said jet is considerably decreased. That is why intercontinental and space rockets are designed as multi-stage ones. Said jet is not suitable for aircraft jet engines. For said purpose there is used a tapering jet with a variable outlet diameter, in which a sound velocity of gas may be achieved at most. There exist controllable jets which are ended with a short extending shape making it possible to achieve a slightly supersonic velocity in a very short scope of a pressure drop; their efficiency is low. Experiments with controlling the critical cross section resulted in technically very complicated designs, being very heavy and having low efficiency.
  • jet the body of which consists of a set of segments, each of them being provided with a separate control lever mechanism.
  • controllable tapering jets behind which usually a controllable or freely adjustable expanding jet is situated.
  • the mentioned drawbacks may be considerably obviated by the supersonic jet with a controllable critical cross section, the principle of which resides in the fact that it comprises a couple of coaxial flanges, arranged one to the other revolvingly and which are interconnected by means of a system ofswingingly fixed lamellas, and at least one flange is seated slidingly.
  • the supersonic jet makes it possible to control the critical cross section of the jet within a wide range of a pressure drop before the jet and behind it, and in this way its complete transformation to a usable kinetic power as well. At the same time there is achieved a maximum efficiency of the supersonic jet within a wide range of the drop of gasses before the jet and behind it.
  • the proper design is simple and makes it possible to use a simple control system
  • one of the flanges is seated fixly and the other one revolvingly.
  • lamellas are partially overlapping, or if each of the lamellas engages, by its front edge, the fork edge arranged at the neighbouring lamella.
  • every lamella at the external side may be provided with a system of longitudinal reinforcements having an open profile in a cross section
  • Fig. 1 - a schematic illustration of the supersonic jet with the controllable critical cross section according to the invention in the position "maximum cross section"
  • Fig. 2 - a section of a supersonic jet in the plane A - A of Fig 1 Fig. 3 - an enlarged (2 1) schematic section of the jet in the plane C - C of Fig. 1 Fig. 4 - a view to a lamella in the direction P of Fig 1 Fig. 5 - a view to a lamella in the direction S of Fig 4 Fig. 6 - an enlarged schematic detail, limited by dash-lines in Fig. 3
  • Fig. 7 - a schematic illustration of the supersonic jet with the controllable critical cross section according to the invention in the position "minimum cross section"
  • Fig. 8 - a section of the supersonic jet in the plane A'-A' of Fig. 7
  • Fig. 9 - an enlarged (2 : 1) schematic section of the jet in the plane C- C of Fig. 7
  • Fig. 10 - a view to a lamella in the direction P' of Fig. 7
  • Fig. 11 - a view to a lamella in the direction S' of Fig. 10
  • FIG. 12 - an enlarged schematic detail, limited by dash-lines in Fig. 9
  • a supersonic jet with a controllable critical cross section according to Fig. 1 consists of a fixed flange 2 and of a swivelling flange 3 which are arranged co-axially.
  • the swivelling flange 3 has a sliding fit too.
  • Both lamellas are interconnected by means of a system of lamellas 1 in such a way that one end of each lamella 1 is swingingly joined to the fixed flange 2 and the other end of each lamella 1 is also swingingly joined to the swivelling flange 3.
  • Longitudinal axis of the lamellas 1 are straight, they form skew lines, and in fact they form surface lines of a rotary hyperboloid.
  • the fixed flange 2 is joined to an outlet part of the jet engine or rocket one, eventually to another source of compressed gas.
  • Every lamellas 1 have, in a cross section (Figs. 6, 12), an open thin wall profile, formed by a body 7 of the lamella 1 with a front edge 5 and with a fork edge 4. Each of the lamellas 1 engages by its front edge 5 in the fork edge 4 of the preceding lamella. So the lamellas form a circular variable cross section of the jet.
  • Each lamella I is provided with longitudinal reinforcements 8, the cross section of which forms an open profile.
  • longitudinal reinforcements 8 the cross section of which forms an open profile.
  • Figs. 6, 12 there is represented the system of the longitudinal reinforcements 8 by two reinforcements arranged longitudinally.
  • Supersonic jets with a controllable critical cross section may be utilised in those cases where it is necessary to achieve a supersonic gas velocity at a variable pressure drop, at observing the optimum control law, especially at rocket engines, aircraft jet engines, double jet engines with a high bypass ratio, eventually as a laboratory equipment

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)

Abstract

La présente invention concerne un jet supersonique à commande de la section critique. Le système comprend deux brides (2, 3), montées de façon à tourner l'une par rapport à l'autre, qui sont reliées au moyen d'un ensemble de lamelles (1) fixées de façon pivotante, et au moins une bride est montée de manière à pouvoir être décalée.
PCT/CZ1996/000013 1995-06-12 1996-06-10 Jet supersonique a commande de la section critique WO1996041940A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AU58086/96A AU5808696A (en) 1995-06-12 1996-06-10 Supersonic jet with a controllable critical cross section

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CZPV1521-95 1995-06-12
CZ951521A CZ152195A3 (en) 1995-06-12 1995-06-12 Supersonic nozzle with controllable critical section

Publications (1)

Publication Number Publication Date
WO1996041940A1 true WO1996041940A1 (fr) 1996-12-27

Family

ID=5463400

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CZ1996/000013 WO1996041940A1 (fr) 1995-06-12 1996-06-10 Jet supersonique a commande de la section critique

Country Status (3)

Country Link
AU (1) AU5808696A (fr)
CZ (1) CZ152195A3 (fr)
WO (1) WO1996041940A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008021618A2 (fr) * 2006-08-18 2008-02-21 General Electric Company Tuyères à géométrie variable à volets multiples

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1198723A (fr) * 1958-02-03 1959-12-09 Snecma Tuyère convergente-divergente à géométrie et sections de col variables d'une façon continue
US3534908A (en) * 1967-11-02 1970-10-20 North American Rockwell Variable geometry nozzle

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1198723A (fr) * 1958-02-03 1959-12-09 Snecma Tuyère convergente-divergente à géométrie et sections de col variables d'une façon continue
US3534908A (en) * 1967-11-02 1970-10-20 North American Rockwell Variable geometry nozzle

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008021618A2 (fr) * 2006-08-18 2008-02-21 General Electric Company Tuyères à géométrie variable à volets multiples
WO2008021618A3 (fr) * 2006-08-18 2008-07-10 Gen Electric Tuyères à géométrie variable à volets multiples
US7802432B2 (en) 2006-08-18 2010-09-28 General Electric Company Multiple vane variable geometry nozzle

Also Published As

Publication number Publication date
AU5808696A (en) 1997-01-09
CZ281516B6 (cs) 1996-10-16
CZ152195A3 (en) 1996-10-16

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