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DE959695C - Gas turbine with rotary atomization - Google Patents

Gas turbine with rotary atomization

Info

Publication number
DE959695C
DE959695C DEB36291A DEB0036291A DE959695C DE 959695 C DE959695 C DE 959695C DE B36291 A DEB36291 A DE B36291A DE B0036291 A DEB0036291 A DE B0036291A DE 959695 C DE959695 C DE 959695C
Authority
DE
Germany
Prior art keywords
combustion chamber
gas turbine
shaped
turbine according
flows
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
DEB36291A
Other languages
German (de)
Inventor
Heinrich Leibach
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.)
BMW Studiengesellschaft fuer Triebwerksbau GmbH
Original Assignee
BMW Studiengesellschaft fuer Triebwerksbau GmbH
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 BMW Studiengesellschaft fuer Triebwerksbau GmbH filed Critical BMW Studiengesellschaft fuer Triebwerksbau GmbH
Priority to DEB36291A priority Critical patent/DE959695C/en
Application granted granted Critical
Publication of DE959695C publication Critical patent/DE959695C/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means

Landscapes

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

Description

Hierzu 1 Blatt Zeichnungen1 sheet of drawings

© €09 618/244 9.56 (609 833 2.57)© € 09 618/244 9.56 (609 833 2.57)

Claims (5)

PATENTANSPRÜCHE: In Betracht gezogene Druckschriften: Französische Patentschrift Nr. 962 862 ; britische Patentschrift Nr. 586556; USA.-Patentschrift Nr. 2694291.CLAIMS: Documents considered: French Patent No. 962,862; British Patent No. 586556; U.S. Patent No. 2694291. 1. Gasturbine mit unmittelbar am Turbinenrad angeordneter Umlaufzerstäubungseinrichtung und mit Ringbrennkammer, dadurch gekennzeichnet, daß die Umlaufzerstäubungseinrichtung außerhalb der Wellenlagerung angeordnet und die Ringbrennkammer in an sich bekannter Weise als Umkehrbrennkammer ausgebildet ist.1. Gas turbine with a circulating atomization device arranged directly on the turbine wheel and with an annular combustion chamber, characterized in that the circulating atomization device arranged outside the shaft bearing and the annular combustion chamber in itself is designed as a reverse combustion chamber in a known manner. 2. Gasturbine nach Anspruch 1, dadurch gekennzeichnet, daß die Zerstäubungseinrichtung aus einer zweiteiligen, mit dem Turbinenrad2. Gas turbine according to claim 1, characterized in that that the atomizing device consists of a two-part, with the turbine wheel (3) rotierenden Topfscheibe (4) besteht, die mit ihrer kegelförmigen Wandung in die ringspaltförmige Brennkammermündung eingreift.(3) rotating cup disk (4), which with its conical wall into the annular gap-shaped Combustion chamber mouth engages. 3. Gasturbine nach Anspruch 1 und 2, dadurch gekennzeichnet, daß in der ringspaltförmigen Brennkammermündung beiderseits der rotierenden kegelförmigen Wandung der Topfscheibe (4) Dralleinsätze (11) od. dgl. derart eingesetzt sind, daß die Verbrennungsluft in die Brennkamer (6) mit entgegengesetzt gerichtetem Drall einströmt.3. Gas turbine according to claim 1 and 2, characterized in that in the annular gap-shaped Combustion chamber mouth on both sides of the rotating conical wall of the Cup disk (4) swirl inserts (11) or the like. Are inserted in such a way that the combustion air flows into the combustion chamber (6) with an oppositely directed swirl. 4. Gasturbine nach Anspruch 1 bis 3, dadurch gekennzeichnet, daß ein Teil der verdichteten Verbrennungsluft durch hohl ausgebildete Turbinenleitschaufeln (8) in den Innenraum (9) und von hier außerhalb der topfformigen Zerstäuberscheibe (4) in die Brennkammer (6) einströmt. 4. Gas turbine according to claim 1 to 3, characterized in that part of the compressed Combustion air through hollow turbine guide vanes (8) into the interior (9) and from here flows into the combustion chamber (6) outside the pot-shaped atomizer disk (4). 5. Gasturbine nach Anspruch 1 bis 4, dadurch gekennzeichnet, daß der übrige Teil der verdichteten Verbrennungsluft durch Bohrungen (10) in das Innere der topfformigen Zerstäuoerscheibe (4) einströmt.5. Gas turbine according to claim 1 to 4, characterized in that the remaining part of the compressed Combustion air through holes (10) into the interior of the pot-shaped atomizer disk (4) flows in.
DEB36291A 1955-06-28 1955-06-29 Gas turbine with rotary atomization Expired DE959695C (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DEB36291A DE959695C (en) 1955-06-28 1955-06-29 Gas turbine with rotary atomization

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE1151430X 1955-06-28
DEB36291A DE959695C (en) 1955-06-28 1955-06-29 Gas turbine with rotary atomization

Publications (1)

Publication Number Publication Date
DE959695C true DE959695C (en) 1957-03-07

Family

ID=25965091

Family Applications (1)

Application Number Title Priority Date Filing Date
DEB36291A Expired DE959695C (en) 1955-06-28 1955-06-29 Gas turbine with rotary atomization

Country Status (1)

Country Link
DE (1) DE959695C (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1179767B (en) * 1958-07-31 1964-10-15 Power Jets Res & Dev Ltd Combustion chamber
US4598544A (en) * 1983-04-28 1986-07-08 Williams International Corporation Medium bypass turbofan engine

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB586556A (en) * 1942-01-12 1947-03-24 Karl Baumann Improvements in internal combustion turbine plant for propulsion
FR962862A (en) * 1946-10-26 1950-06-22
US2694291A (en) * 1948-02-07 1954-11-16 Henning C Rosengart Rotor and combustion chamber arrangement for gas turbines

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB586556A (en) * 1942-01-12 1947-03-24 Karl Baumann Improvements in internal combustion turbine plant for propulsion
FR962862A (en) * 1946-10-26 1950-06-22
US2694291A (en) * 1948-02-07 1954-11-16 Henning C Rosengart Rotor and combustion chamber arrangement for gas turbines

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1179767B (en) * 1958-07-31 1964-10-15 Power Jets Res & Dev Ltd Combustion chamber
US4598544A (en) * 1983-04-28 1986-07-08 Williams International Corporation Medium bypass turbofan engine

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