DE3302318A1 - Gas turbine - Google Patents

Gas turbine

Info

Publication number
DE3302318A1
DE3302318A1 DE19833302318 DE3302318A DE3302318A1 DE 3302318 A1 DE3302318 A1 DE 3302318A1 DE 19833302318 DE19833302318 DE 19833302318 DE 3302318 A DE3302318 A DE 3302318A DE 3302318 A1 DE3302318 A1 DE 3302318A1
Authority
DE
Germany
Prior art keywords
blades
turbine wheel
air compressor
air
aircraft
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.)
Withdrawn
Application number
DE19833302318
Other languages
German (de)
Inventor
Franz-Josef Weber
Original Assignee
Weber Franz Josef
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 Weber Franz Josef filed Critical Weber Franz Josef
Priority to DE19833302318 priority Critical patent/DE3302318A1/en
Publication of DE3302318A1 publication Critical patent/DE3302318A1/en
Withdrawn legal-status Critical Current

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/045Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor having compressor and turbine passages in a single rotor-module
    • F02C3/05Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor having compressor and turbine passages in a single rotor-module the compressor and the turbine being of the radial flow type
    • Y02T50/671

Abstract

Gas turbines are also manufactured with radial blades as heat engines. They also require an air compressor with a long shaft. Their component cost is still too high and thereby prevents reduction of the production costs. Their metal turbine wheel blades can only be exposed to temperatures of up to 1050 DEG C and those of ceramic up to 1350 DEG C, at which their power limit is reached. The present gas turbine has only one wheel disc as common carrier of the air compressor and turbine wheel blades. Cooling air annular nozzles are directed at the turbine wheel blades, which nozzles are connected to the air compressor. In a post-connected turbine wheel heat exchanger the exhaust gases, due to the air circulation on the aircraft hollow-profile blades, transmit intense heat to the fresh air for the combustion chamber. It is intended for use as a single engine in light aircraft, motor boats, units and car wash systems, as a compound engine in passenger aircraft, buses, trucks, motor yachts and large machine units.
DE19833302318 1983-01-25 1983-01-25 Gas turbine Withdrawn DE3302318A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DE19833302318 DE3302318A1 (en) 1983-01-25 1983-01-25 Gas turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19833302318 DE3302318A1 (en) 1983-01-25 1983-01-25 Gas turbine

Publications (1)

Publication Number Publication Date
DE3302318A1 true DE3302318A1 (en) 1983-08-04

Family

ID=6189107

Family Applications (1)

Application Number Title Priority Date Filing Date
DE19833302318 Withdrawn DE3302318A1 (en) 1983-01-25 1983-01-25 Gas turbine

Country Status (1)

Country Link
DE (1) DE3302318A1 (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3339505A1 (en) * 1983-10-31 1985-05-09 Bernd Jung Gas turbine with turbocompressor connected on the inlet side
WO1997038218A2 (en) * 1996-04-04 1997-10-16 Nadine Jung Gas-turbine unit
DE19617539A1 (en) * 1996-05-02 1997-11-13 Asea Brown Boveri Rotor for thermal turbo engine

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3339505A1 (en) * 1983-10-31 1985-05-09 Bernd Jung Gas turbine with turbocompressor connected on the inlet side
WO1997038218A2 (en) * 1996-04-04 1997-10-16 Nadine Jung Gas-turbine unit
WO1997038218A3 (en) * 1996-04-04 1997-12-11 Nadine Jung Gas-turbine unit
DE19617539A1 (en) * 1996-05-02 1997-11-13 Asea Brown Boveri Rotor for thermal turbo engine
DE19617539B4 (en) * 1996-05-02 2006-02-09 Alstom Rotor for a thermal turbomachine

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Legal Events

Date Code Title Description
OAV Applicant agreed to the publication of the unexamined application as to paragraph 31 lit. 2 z1
OP8 Request for examination as to paragraph 44 patent law
8130 Withdrawal