DE612362C - Rocket with the air duct surrounding the combustion chamber - Google Patents

Rocket with the air duct surrounding the combustion chamber

Info

Publication number
DE612362C
DE612362C DEG85505D DEG0085505D DE612362C DE 612362 C DE612362 C DE 612362C DE G85505 D DEG85505 D DE G85505D DE G0085505 D DEG0085505 D DE G0085505D DE 612362 C DE612362 C DE 612362C
Authority
DE
Germany
Prior art keywords
combustion chamber
air duct
rocket
air
duct surrounding
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.)
Expired
Application number
DEG85505D
Other languages
German (de)
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.)
E H GUSTAV DE GRAHL DR ING
Original Assignee
E H GUSTAV DE GRAHL DR ING
Publication date
Priority to DEG85505D priority Critical patent/DE612362C/en
Application granted granted Critical
Publication of DE612362C publication Critical patent/DE612362C/en
Expired legal-status Critical Current

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
    • F02K7/10—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 characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
    • F02K7/12—Injection-induction jet engines

Landscapes

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

Description

Rakete mit die Brennkammer umgebendem Luftleitkanal Die Erfindung hat eine besondere Ausbildung des die Brennkammer von Raketengeschossen umgebenden Luftleitkanals zum Gegenstande. Die bekannten Raketen neigen infolge nicht genügender Mischung oder zu starker Abkühlung der Luft zu starker Rauchentwicklung, so daß eine vollständige Verbrennung nicht eintritt. Wird feiner der Luftleitkanal vollständig gleichförmig in der Brennkammerzone durchgeführt, so erfährt infolge der zunehmenden Erwärmung die Verbrennungsluft eine größere Raumausdehnung, die zu Rückstauungen und Explosionen führen kann. Um diese Nachteile zu vermeiden, wird der Sprengstoff und der Treibmittelsatz mit einem an der Stirnseite offenen Luftleitkanal umgeben, der in der Brennkaminerzone des Geschosses eine Erweiterung erhält, um die Geschwindigkeit der eingepreßten und angesaugten Luft herabzusetzen und damit die Widerstände und sonstigen Gefahrenquellen zu verringern. Weiterhin wird die angesaugte Luft an Rippenheizflächen vorbeigeführt, an denen sie stufenweise erhitzt und durch Unterteilung in einzelne Luftströme stufenweise den Treibmittelgasen zugeführt wird.Rocket with the air duct surrounding the combustion chamber. The invention has a special design that surrounds the combustion chamber of rocket projectiles Air duct to the subject. The known rockets tend not enough Mixing or cooling the air too much, too much smoke development, so that complete combustion does not occur. The air duct becomes finer completely carried out uniformly in the combustion chamber zone, as a result of the increasing The combustion air heats up a larger room, which leads to backwater and cause explosions. To avoid these disadvantages, the explosives and the propellant set is surrounded by an air duct open at the front, which in the chimney zone of the projectile is expanded to include the speed reduce the forced-in and sucked-in air and thus the resistances and to reduce other sources of danger. Furthermore, the sucked in air is on rib heating surfaces Passed by, which they gradually heated and divided into individual Air flows are gradually fed to the propellant gases.

In der Abbildung ist eine Ausführungsform des Gegenstandes der Erfindung dargestellt.In the figure is an embodiment of the subject invention shown.

In dieser enthält der obere Behälter den Sprengstoff und der anschließende Behälter den Treibmittelsatz. B ist die Brenndüse. Der Brennstoff- und Treibmittelsatz sind von dem Luftleitkanal I( umgeben, welcher mit der Außenluft an den offenen Stirnseiten in Verbindung steht. Der LuftleitkanalI( ist in der Brennkammerzone erweitert und mit den Heizrippen R versehen, an denen die angesaugte Luft für den Verbrennungsvorgang vorgewärmt und stufenweise zur Mischung den Treibmittelgasen zugeführt wird.In this, the upper container contains the explosives and the subsequent one Container the propellant kit. B is the nozzle. The fuel and propellant set are surrounded by the air duct I (, which connects with the outside air to the open Front sides is in connection. The air duct I (is in the combustion chamber zone expanded and provided with the heating ribs R, where the sucked in air for the Preheated combustion process and gradually mixing the propellant gases is fed.

Claims (1)

PATENTANSPRUCH: Rakete mit die Brennkammer umgebendem Luftleitkanal und einer Reihe von Luftmischdüsen hinter der Brennkammer, dadurch gekennzeichnet, daß der Luftleitkanal in der Brennkammerzone erweitert und mit Heizrippen versehen ist.PATENT CLAIM: Rocket with air duct surrounding the combustion chamber and a series of air mixing nozzles behind the combustion chamber, characterized in that that the air duct in the combustion chamber zone is expanded and provided with heating ribs is.
DEG85505D Rocket with the air duct surrounding the combustion chamber Expired DE612362C (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DEG85505D DE612362C (en) Rocket with the air duct surrounding the combustion chamber

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DEG85505D DE612362C (en) Rocket with the air duct surrounding the combustion chamber

Publications (1)

Publication Number Publication Date
DE612362C true DE612362C (en) 1935-04-18

Family

ID=7138216

Family Applications (1)

Application Number Title Priority Date Filing Date
DEG85505D Expired DE612362C (en) Rocket with the air duct surrounding the combustion chamber

Country Status (1)

Country Link
DE (1) DE612362C (en)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2547936A (en) * 1944-11-17 1951-04-10 Harlow B Grow Ducted rocket propulsion means for aircraft
US2605608A (en) * 1946-06-27 1952-08-05 Jr Frank D Barclay Jet reaction motor
US2641902A (en) * 1947-09-13 1953-06-16 Curtiss Wright Corp Combination ram jet and turbojet
US2867979A (en) * 1946-04-29 1959-01-13 Experiment Inc Apparatus for igniting fuels
DE1104867B (en) * 1958-02-11 1961-04-13 J G W Berckholtz Fa Rocket with stabilizer
US2999672A (en) * 1958-04-09 1961-09-12 Curtiss Wright Corp Fluid mixing apparatus
US3442086A (en) * 1967-10-19 1969-05-06 Hilbert W Nieman Jet type air motor
FR2519377A1 (en) * 1977-02-08 1983-07-08 Messerschmitt Boelkow Blohm STATOREACTOR, PARTICULARLY COMBUSTIBLES CONTAINING, IN THE FORM OF PARTICLES, BORON OR OTHER ENERGY MATERIALS OF HIGH TEMPERATURE OF FUSION AND VAPORIZATION
FR2839117A1 (en) * 2002-04-30 2003-10-31 Khalid Ouachkradi Improvement of air catchment of air take-off rocket utilizes gas energy supplied by rocket rich in fuel to improve nozzle effect and increase contact surface between gas and induced fresh air
WO2004063549A1 (en) * 2003-01-13 2004-07-29 The Texas A & M University System Jet ejector and method of altering fluid flow

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2547936A (en) * 1944-11-17 1951-04-10 Harlow B Grow Ducted rocket propulsion means for aircraft
US2867979A (en) * 1946-04-29 1959-01-13 Experiment Inc Apparatus for igniting fuels
US2605608A (en) * 1946-06-27 1952-08-05 Jr Frank D Barclay Jet reaction motor
US2641902A (en) * 1947-09-13 1953-06-16 Curtiss Wright Corp Combination ram jet and turbojet
DE1104867B (en) * 1958-02-11 1961-04-13 J G W Berckholtz Fa Rocket with stabilizer
US2999672A (en) * 1958-04-09 1961-09-12 Curtiss Wright Corp Fluid mixing apparatus
US3442086A (en) * 1967-10-19 1969-05-06 Hilbert W Nieman Jet type air motor
FR2519377A1 (en) * 1977-02-08 1983-07-08 Messerschmitt Boelkow Blohm STATOREACTOR, PARTICULARLY COMBUSTIBLES CONTAINING, IN THE FORM OF PARTICLES, BORON OR OTHER ENERGY MATERIALS OF HIGH TEMPERATURE OF FUSION AND VAPORIZATION
FR2839117A1 (en) * 2002-04-30 2003-10-31 Khalid Ouachkradi Improvement of air catchment of air take-off rocket utilizes gas energy supplied by rocket rich in fuel to improve nozzle effect and increase contact surface between gas and induced fresh air
WO2004063549A1 (en) * 2003-01-13 2004-07-29 The Texas A & M University System Jet ejector and method of altering fluid flow
US7780099B2 (en) 2003-01-13 2010-08-24 The Texas A&M University System High-efficiency jet ejector and propulsive jet

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