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DE3520015A1 - Nozzle arrangement in the case of a powerplant - Google Patents

Nozzle arrangement in the case of a powerplant

Info

Publication number
DE3520015A1
DE3520015A1 DE19853520015 DE3520015A DE3520015A1 DE 3520015 A1 DE3520015 A1 DE 3520015A1 DE 19853520015 DE19853520015 DE 19853520015 DE 3520015 A DE3520015 A DE 3520015A DE 3520015 A1 DE3520015 A1 DE 3520015A1
Authority
DE
Germany
Prior art keywords
chamber
same
nozzle
larger
nozzle arrangement
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
DE19853520015
Other languages
German (de)
Inventor
Gerhard Nerenberg
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Priority to DE19853520015 priority Critical patent/DE3520015A1/en
Publication of DE3520015A1 publication Critical patent/DE3520015A1/en
Ceased 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
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
    • F02K9/32—Constructional parts; Details not otherwise provided for
    • F02K9/34—Casings; Combustion chambers; Liners thereof
    • 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
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
    • F02K9/30—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants with the propulsion gases exhausting through a plurality of nozzles
    • 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
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/60—Constructional parts; Details not otherwise provided for
    • F02K9/62—Combustion or thrust chambers
    • 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
    • F02K9/97—Rocket nozzles

Landscapes

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

Abstract

The invention represents a nozzle arrangement for a powerplant, which nozzle arrangement produces a modified rocket reaction thrust. The combustion jet of a high-pressure powerplant is passed into a flat, large-area chamber and is here ejected from a large number of small nozzles. The reaction thrust is also greater, corresponding to the larger reaction surface of the new chamber.

Description

1. Mit Hilfe eines leistungsstarken Triebwerkes (Radialver­ dichtertriebwerk), und einer besonderen Düsenanordnung, bestehend aus einer flachen Druckkammer mit vielen Einzel­ düsen, also einer Kombination aus Triebwerk und umgeändertem Raktenrückstoß.1. With the help of a powerful engine (radial ver density engine), and a special nozzle arrangement, consisting of a flat pressure chamber with many individual nozzles, i.e. a combination of engine and modified Missile recoil.

2. Der überschüssige Gasstrahl wird nicht nur waagerecht aus einer einfachen Düse ausgestoßen, auch nicht einfach umge­ lenkt in die senkrechte Richtung, wie bei den bisherigen Senkrechtstartern, sondern dazu benutzt in einer besonderen Reaktionskammer einen Rückstoß nach Raketenart zu erzeugen.2. The excess gas jet is not only horizontal ejected through a simple nozzle, not just vice versa steers in the vertical direction, as with the previous ones Whiz, but used in a special way Reaction chamber to generate a rocket-type recoil.

3. Wenn eine Raketenbrennkammer bisheriger Bauart in eine andere Form gebracht wird und hier der Gasstrahl hinein geleitet wird, der noch genügend Druck hat, wird ein größerer Rück­ stoß erzeugt.3. If a rocket combustor of the previous design into another Is brought into shape and the gas jet is directed into it who has enough pressure will have a bigger back thrust generated.

4. Die neue Druckkammer erhält eine flache, rechteckige Form. Die große Düse der bisherigen Form wird aufgeteilt in viele kleine Düsen und über der Fläche verteilt. Beim Vergleich beider Druckkammertypen sind beide Rauminhalte gleich, die Summe der Querschnitte der kleinen Düsen ist gleich dem Querschnitt der großen Einzeldüse.4. The new pressure chamber is given a flat, rectangular shape. The large nozzle of the previous form is divided into many small nozzles and spread over the area. When comparing Both types of pressure chamber have the same volume, that The sum of the cross sections of the small nozzles is equal to that Cross section of the large single nozzle.

5. Bei gleicher Gasbeaufschlagung wäre die Austrittsgeschwindig­ keit bei beiden gleich. Die Wirkungsfläche in Bewegungsrich­ tung der flachen Bauart ist aber größer als die der runden Kammer. Der Rückstoß ist ebenfalls größer.5. With the same gas supply, the exit would be speedy same for both. The effective area in the direction of motion The flat design is larger than that of the round one Chamber. The recoil is also greater.

6. Es findet eine Kraftverstärkung statt, wie im anderen Kraftverstärker.6. There is an increase in power as in the other Power booster.

Claims (4)

1. Düsenanordnung bei einem Triebwerk, dadurch gekennzeichnet, daß der überschüssige Brennstrahl eines druckstarken Trieb­ werkes nicht wie bisher bei Senkrechtstartern einfach um 90 Grad nach unten umgelenkt wird, sondern in eine Druck­ kammer geleitet wird.1. Nozzle arrangement in an engine, characterized in that the excess fuel jet of a powerful engine is not simply diverted by 90 degrees downwards as previously with vertical starters, but is passed into a pressure chamber. 2. Diese stellt eine umgeänderte Form einer Raketenbrennkammer dar. Sie ist eine flache rechteckige Kammer mit gleichem Volumen wie eine herkömmliche Raketenkammer für gleichen Gasdurchsatz. An Stelle einer einzigen großen Düse bei der alten Form, erhält die neue Kammer viele kleine Düsen auf die größere Fläche verteilt.2. This represents a modified form of a missile combustion chamber It is a flat rectangular chamber with the same Volume like a conventional missile chamber for the same Gas flow. Instead of a single large nozzle in the old shape, the new chamber receives many small nozzles spread the larger area. 3. Die Summe der Düsenquerschnitte der kleinen Düsen, ist gleich dem Querschnitt der einzelnen großen Düse der alten Form. Bei gleicher Gasbeaufschlagung würde die Austrittsgeschwin­ digkeit bei beiden Anordnungen gleich sein.3. The sum of the nozzle cross-sections of the small nozzles is the same the cross section of the single large nozzle of the old form. With the same gas supply, the exit speed would be the same in both arrangements. 4. Die Reaktionsfläche der neuen Form ist aber größer als die der alten Form. Der Rückstoß ist der größeren Fläche entsprechend auch größer.4. The reaction area of the new form is larger than that of the old form. The recoil is the larger area accordingly also larger.
DE19853520015 1985-06-04 1985-06-04 Nozzle arrangement in the case of a powerplant Ceased DE3520015A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DE19853520015 DE3520015A1 (en) 1985-06-04 1985-06-04 Nozzle arrangement in the case of a powerplant

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19853520015 DE3520015A1 (en) 1985-06-04 1985-06-04 Nozzle arrangement in the case of a powerplant

Publications (1)

Publication Number Publication Date
DE3520015A1 true DE3520015A1 (en) 1987-01-08

Family

ID=6272413

Family Applications (1)

Application Number Title Priority Date Filing Date
DE19853520015 Ceased DE3520015A1 (en) 1985-06-04 1985-06-04 Nozzle arrangement in the case of a powerplant

Country Status (1)

Country Link
DE (1) DE3520015A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102005002283A1 (en) * 2004-11-20 2006-11-09 SCHÄFER, Alexander Rocket propulsion, has combustion chamber including thrust pipe, where thrust pipe is spaced out simultaneously with presonic velocities of gas and also with supersonic velocities

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1481642A1 (en) * 1965-07-23 1970-01-22 Rolls Royce Improved vertical lift gas turbine jet aircraft
GB1252077A (en) * 1969-03-08 1971-11-03
JPS56129743A (en) * 1980-03-14 1981-10-12 Minoru Yamaguchi Jet engine with thrust multiplying nozzle

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1481642A1 (en) * 1965-07-23 1970-01-22 Rolls Royce Improved vertical lift gas turbine jet aircraft
GB1252077A (en) * 1969-03-08 1971-11-03
JPS56129743A (en) * 1980-03-14 1981-10-12 Minoru Yamaguchi Jet engine with thrust multiplying nozzle

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102005002283A1 (en) * 2004-11-20 2006-11-09 SCHÄFER, Alexander Rocket propulsion, has combustion chamber including thrust pipe, where thrust pipe is spaced out simultaneously with presonic velocities of gas and also with supersonic velocities

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Legal Events

Date Code Title Description
OP8 Request for examination as to paragraph 44 patent law
8131 Rejection