DE1189319B - Back pressure turbine with ramjet engines - Google Patents

Back pressure turbine with ramjet engines

Info

Publication number
DE1189319B
DE1189319B DESCH32629A DESC032629A DE1189319B DE 1189319 B DE1189319 B DE 1189319B DE SCH32629 A DESCH32629 A DE SCH32629A DE SC032629 A DESC032629 A DE SC032629A DE 1189319 B DE1189319 B DE 1189319B
Authority
DE
Germany
Prior art keywords
back pressure
engines
disk
pressure turbine
ramjet engines
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.)
Pending
Application number
DESCH32629A
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.)
GUENTER SCHEFFLER DIPL ING
Original Assignee
GUENTER SCHEFFLER DIPL ING
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 GUENTER SCHEFFLER DIPL ING filed Critical GUENTER SCHEFFLER DIPL ING
Priority to DESCH32629A priority Critical patent/DE1189319B/en
Publication of DE1189319B publication Critical patent/DE1189319B/en
Pending legal-status Critical Current

Links

Classifications

    • 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
    • F02C3/16—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 chambers being formed at least partly in the turbine rotor or in an other rotating part of the plant
    • F02C3/165—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 chambers being formed at least partly in the turbine rotor or in an other rotating part of the plant the combustion chamber contributes to the driving force by creating reactive thrust

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

Rückdruckturbine mit Staustrahltriebwerken Die Erfindung betrifft eine Rückdruckturbine mit Staustrahltriebwerken, die am Umfang einer rotierenden Scheibe od. dgl. schräg zur Drehachse der Scheibe angeordnet sind, wobei der Scheibe od. dgl. eine zweite Turbinenscheibe od. dgl. nachgeschaltet ist, die von den Auspuffgasen der Triebwerke der ersten Scheibe od. dgl. in entgegengesetzter Richtung angetrieben wird.Back pressure turbine with ramjet engines The invention relates to a back pressure turbine with ramjet engines rotating on the circumference of a Disc od. The like. Are arranged obliquely to the axis of rotation of the disc, the disc or the like. A second turbine disk or the like. Is connected downstream from the exhaust gases the drives of the first disc or the like. Driven in the opposite direction will.

Die Erfindung hat eine besonders zweckmäßige Ausgestaltung zum Gegenstand, durch welche der Wirkungsgrad wesentlich verbessert wird.The subject of the invention is a particularly expedient embodiment, through which the efficiency is significantly improved.

In Weiterentwicklung der bekannten Ausführungen dieser Art wird gemäß der Erfindung in den Staustahltriebwerken in an sich bekannter Weise der Sauerstoffanteil der Luft von dem Stickstoffanteil durch Zentrifugalkraft getrennt und der Sauerstoff der Brennkammer zugeleitet, während der Stickstoff zur Kühlung der Düsen dient. Die Anwendung der an sich bekannten Trennung der Luft in einen Sauerstoffanteil und einen Stickstoffanteil durch Zentrifugalkraft bei Rückdruckturbinen mit Staustrahltriebwerken bringt den Vorteil, daß der Stickstoffanteil nicht der Brennkammer zugeleitet werden muß und daher auch nicht erwärmt zu werden braucht. Da nur Sauerstoff und Brennstoff zur Verbrennung gelangen, ist der Wirkungsgrad der Verbrennung erheblich größer. Außerdem wird auch die Kühlung der Strahltriebwerke wesentlich verbessert.In a further development of the known designs of this type, according to the invention in the ram steel engines in a known manner the oxygen content the air is separated from the nitrogen content by centrifugal force and the oxygen fed to the combustion chamber, while the nitrogen is used to cool the nozzles. The use of the known separation of air into an oxygen component and a nitrogen content from centrifugal force in back pressure turbines with ramjet engines has the advantage that the nitrogen content is not fed into the combustion chamber must and therefore does not need to be heated. Since only oxygen and fuel reach combustion, the combustion efficiency is considerably greater. In addition, the cooling of the jet engines is also significantly improved.

Der Gegenstand der Erfindung ist in der Zeichnung an Hand eines Ausführungsbeispieles näher erläutert, und zwar zeigt F i g. 1 einen mittleren Längsschnitt einer schematisch dargestellten Rückdruckturbine mit Staustrahltriebwerken, F i g. 2 den Gegenstand der F i g. 1 in einer seitlichen Ansicht und F i g. 3 eine Draufsicht auf ein Staustrahltriebwerk. Auf einer zweckmäßig hohlen Welle 1 sitzt ein Laufrad 2 mit einer Anzahl schräg eingebauter Verdichtungsdüsen 3, die die Aufgaben haben, die mit hoher Geschwindigkeit eintretende Luft zu verdichten.The object of the invention is shown in the drawing using an exemplary embodiment explained in more detail, namely shows F i g. 1 is a central longitudinal section of a schematic illustrated back pressure turbine with ramjet engines, F i g. 2 the subject the F i g. 1 in a side view and FIG. 3 is a plan view of a ramjet engine. On an expediently hollow shaft 1, an impeller 2 sits obliquely with a number built-in compression nozzles 3, which do the jobs at high speed compressing incoming air.

Die Düse 3 ist gemäß der Erfindung durch Anordnung einer Trennwand 5 so ausgebildet, daß durch die Zentrifugalkraft der Sauerstoff auf Grund seines höheren spezifischen Gewichtes von dem Stickstoff getrennt und nur der Sauerstoff der Brenndüse zugeleitet wird. Der abgeschiedene Stickstoff dient zur Kühlung der Düse. Der Kraftstoff wird mit Hilfe der Zentrifugalkraft durch das Rohr 4 in die äußere, durch die Trennwand 5 gebildete Düsenkammer geleitet, in welcher der Sauerstoff enthalten ist.The nozzle 3 is designed according to the invention by arranging a partition 5 so that the centrifugal force separates the oxygen from the nitrogen due to its higher specific weight and only the oxygen is fed to the combustion nozzle. The separated nitrogen is used to cool the nozzle. With the help of centrifugal force, the fuel is passed through the pipe 4 into the outer nozzle chamber formed by the partition wall 5, in which the oxygen is contained.

Claims (1)

Patentanspruch: Rückdruckturbine mit Staustrahltriebwerken, die am Umfang einer rotierenden Scheibe od. dgl. schräg zur Drehachse der Scheibe angeordnet sind, wobei der Scheibe od. dgl. eine zweite Turbinenscheibe od. dgl. nachgeschaltet ist, die von den Auspuffgasen der Triebwerke der ersten Scheibe od. dgl. in entgegengesetzter Richtung angetrieben wird, dadurch gekennzeichn e t, daß in den Staustrahltriebwerken der Sauerstoffanteil der Luft von dem Stickstoffanteil durch Zentrifugalkraft getrennt wird und daß der Sauerstoff der Brennkammer zugeleitet wird, während der Stickstoff zur Kühlung der Düsen dient. -In Betracht gezogene Druckschriften: Deutsche Patentschriften Nr. 399 620, 917120; französische Patentschriften Nr. 863 484, 934 755, Zusatzpatent 57 691 zu Nr. 934 755, 958183, 1037 907; britische Patentschrift Nr. 645 641; USA.-Patentschriften Nr. 2 603 947, 2 637166, 2 644 301, 2 917 895, 2 994195; Buch von Eyermann-Schulz, »Gasturbinen«, 1920, S. 124 bis 131, 239 bis 256.Claim: back pressure turbine with ramjet engines, which on Perimeter of a rotating disk or the like. Arranged obliquely to the axis of rotation of the disk are, whereby the disk or the like is followed by a second turbine disk or the like is that of the exhaust gases of the engines of the first disc od. Like. In opposite Direction is driven, characterized in that in the ramjet engines the oxygen content of the air is separated from the nitrogen content by centrifugal force and that the oxygen is fed to the combustion chamber, while the nitrogen serves to cool the nozzles. -Considered publications: German patents No. 399 620, 917120; French patents nos. 863 484, 934 755, additional patent 57 691 to No. 934 755, 958183, 1037 907; British Patent No. 645,641; U.S. Patents No. 2,603,947, 2,637,166, 2,644,301, 2,917,895, 2,994,195; Book by Eyermann-Schulz, "Gas turbines", 1920, pp. 124 to 131, 239 to 256.
DESCH32629A 1963-01-22 1963-01-22 Back pressure turbine with ramjet engines Pending DE1189319B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DESCH32629A DE1189319B (en) 1963-01-22 1963-01-22 Back pressure turbine with ramjet engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DESCH32629A DE1189319B (en) 1963-01-22 1963-01-22 Back pressure turbine with ramjet engines

Publications (1)

Publication Number Publication Date
DE1189319B true DE1189319B (en) 1965-03-18

Family

ID=7432510

Family Applications (1)

Application Number Title Priority Date Filing Date
DESCH32629A Pending DE1189319B (en) 1963-01-22 1963-01-22 Back pressure turbine with ramjet engines

Country Status (1)

Country Link
DE (1) DE1189319B (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3522703A (en) * 1968-01-02 1970-08-04 Ferenc Toth Multistage tangential turbine

Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE399620C (en) * 1924-07-25 Eduard Mazza Process for separating gaseous mixtures into their components by centrifugal force
FR863484A (en) * 1939-11-08 1941-04-02 Rocket engine
FR934755A (en) * 1946-10-14 1948-06-01 Thermal engine with rotating nozzles
FR958183A (en) * 1950-03-04
GB645641A (en) * 1948-07-26 1950-11-08 Wadsworth Walton Mount Improvements in or relating to the production of power
US2603947A (en) * 1947-12-13 1952-07-22 Kenneth C Howard Continuous combustion type rotating combustion products generator
FR57691E (en) * 1947-10-01 1953-05-04 Thermal engine with rotating nozzles
US2637166A (en) * 1948-10-07 1953-05-05 James M Carswell Pure reaction turbine with evacuated chamber and rotor element therefor
US2644301A (en) * 1949-02-08 1953-07-07 Karlby Henning Ram jet turbine
FR1037907A (en) * 1951-05-30 1953-09-23 Snecma Jet thruster
DE917120C (en) * 1942-07-03 1954-08-26 Leon Joseph Dubois Container in the form of a spheroid
US2917895A (en) * 1956-12-13 1959-12-22 Homer A Boushey Jet propelled propeller or rotor blade
US2994195A (en) * 1959-04-02 1961-08-01 James M Carswell Jet reaction prime mover

Patent Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE399620C (en) * 1924-07-25 Eduard Mazza Process for separating gaseous mixtures into their components by centrifugal force
FR958183A (en) * 1950-03-04
FR863484A (en) * 1939-11-08 1941-04-02 Rocket engine
DE917120C (en) * 1942-07-03 1954-08-26 Leon Joseph Dubois Container in the form of a spheroid
FR934755A (en) * 1946-10-14 1948-06-01 Thermal engine with rotating nozzles
FR57691E (en) * 1947-10-01 1953-05-04 Thermal engine with rotating nozzles
US2603947A (en) * 1947-12-13 1952-07-22 Kenneth C Howard Continuous combustion type rotating combustion products generator
GB645641A (en) * 1948-07-26 1950-11-08 Wadsworth Walton Mount Improvements in or relating to the production of power
US2637166A (en) * 1948-10-07 1953-05-05 James M Carswell Pure reaction turbine with evacuated chamber and rotor element therefor
US2644301A (en) * 1949-02-08 1953-07-07 Karlby Henning Ram jet turbine
FR1037907A (en) * 1951-05-30 1953-09-23 Snecma Jet thruster
US2917895A (en) * 1956-12-13 1959-12-22 Homer A Boushey Jet propelled propeller or rotor blade
US2994195A (en) * 1959-04-02 1961-08-01 James M Carswell Jet reaction prime mover

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3522703A (en) * 1968-01-02 1970-08-04 Ferenc Toth Multistage tangential turbine

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