DE1189319B - Back pressure turbine with ramjet engines - Google Patents
Back pressure turbine with ramjet enginesInfo
- 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
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)
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)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3522703A (en) * | 1968-01-02 | 1970-08-04 | Ferenc Toth | Multistage tangential turbine |
Citations (13)
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 |
-
1963
- 1963-01-22 DE DESCH32629A patent/DE1189319B/en active Pending
Patent Citations (13)
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)
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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