Heinkel HeS 1
The Heinkel HeS 1 , short for He inkel S trahltriebwerk 1 , was a jet engine from Ernst Heinkel Flugzeugwerke , which was designed in Germany before the Second World War . There was no flight operation. On the basis of this engine, the Heinkel HeS 3 engine was later developed, with which the first flight was completed exclusively with a jet engine.
History / garage model
The idea behind the engine was Hans Joachim Pabst von Ohain , who from 1930 studied aerodynamics and physics in Göttingen, Rostock and Berlin, but was also interested in aviation as a glider pilot. In 1935 he received his doctorate at the 1st Physics Institute of the Georg-August University of Göttingen under his doctoral supervisor Robert Wichard Pohl . He and the aerodynamicist Prof. Ludwig Prandtl , who teaches at the same university , became his sponsors.
Starting in 1933, while working as a doctoral student, he developed ideas for turbojet engines based on the structure and operating principle of a Nernst turbine, which he substantiated with calculations. In 1935 a patent was applied for to protect his ideas and work. The patent was issued in 1937 under the title Method and Apparatus for Producing Air Currents for Propelling Aircraft under the number 317/18. The engine described therein consisted of a two-stage compressor with an axial and a radial stage, an annular space combustion chamber with 8 burners arranged in the circumferential direction and a radial turbine. It is unclear whether von Ohain was already aware of Frank Whittle's patent from 1930 with a comparable engine structure. Von Ohain personally assured that he only found out about it in 1937, two years after the patent was filed.
In 1935, von Ohain and his auto mechanic Max Hahn built the demonstration engine, later known as the garage model , with which the concept of turbojet engines was to be examined. The cost of 1,000 Reichsmarks was partially covered by his grandmother. The tests were carried out in the back yard of the Physikalisches Institut in order to be able to use its measurement technology. Problems with the combustion occurred during these tests, so that the engine did not run by itself. The gasoline chosen as fuel burned in the turbine and the exhaust nozzle instead of in the combustion chamber. This in turn led to overheating of an electric motor, which was supposed to keep the engine at a speed of 8000 rpm.
Development of the HeS 1 at Heinkel
Pohl recognized the potential of the concept and advised an industrial partner. Von Ohain mistrusted traditional engine manufacturers and favored Heinkel, an aircraft manufacturer whose readiness to take development risks he knew. In February 1936, Pohl made contact with Ernst Heinkel . He was interested and organized a meeting with his engineers, at which von Ohain was supposed to present his work. Even if the garage model was not a success, the potential was recognized and von Ohain hired him in April 1936, followed by Max Hahn later.
First of all, work was continued on the garage model and the cause of the combustion problems was found out. The air mass flow between the compressor and turbine did not work as expected and backflows occurred in the compressor. It was decided to build a new demonstrator and operate it with hydrogen.
The development of the HeS 1 took place in secrecy on the premises of the Ernst Heinkel Flugzeugwerke in Rostock-Marienehe . The work was significantly supported by Heinkel engineer Wilhelm Gundermann together with another 6 to 8 designers and calculation engineers as well as 6 to 8 mechanics under the leadership of Max Hahn.
The HeS 1 was further developed compared to the garage model. Instead of an almost pure, but simplified sheet metal construction favored by Hahn (including that of the compressor and the combustion chamber), the HeS 1 was increasingly built from cast and milled parts, but also more complex sheet metal parts. The combustion chamber was positioned outside of the compressor contour and lengthened to enable better burnout. The principle of a two-stage compressor with an axial and a radial stage and a single-stage radial turbine was also used. However, both assemblies were separated, i.e. H. positioned at a greater distance from each other. This should improve the flow behavior in the entire engine.
Tests in March 1937 showed that the engine ran very well. Only the combustion caused problems because the hydrogen burned the metal, which was unacceptable for flight operations. Under pressure from Ernst Heinkel, a solution was found by September 1937 in which - again, liquid fuel - was better atomized in the combustion chamber. In parallel to the work on HeS 1, the development of an HeS 2 and finally that of the Heinkel HeS 3 began, with which the first flight was completed exclusively with a jet engine in September 1939.
Technical specifications
| Data | Heinkel HeS 1 |
|---|---|
| Type | Turbojet |
| Start thrust | 136 kp (1.33 kN) (1.1 kN after) |
| rotational speed | 10,000 rpm |
| Rotor diameter | 0.61 m |
| Diameter complete | 0.905 m |
| length | 0.9 m |
| compressor | 2 stages (1 × axial, 1 × radial) |
| turbine | 1 radial step |
| annotation | Data after |
literature
- Antony Kay: German Jet Engine and Gas Turbine Development 1930–1945 . Airlife Publishing Ltd, Shrewsbury 2002, ISBN 1-84037-294-X (English).
- Willy JG Bräunling: aircraft engines . Basics, aero-thermodynamics, ideal and real cycle processes, thermal turbo machines, components, emissions and systems. 3. Edition. Springer, Berlin 2009, ISBN 978-3-540-76368-0 .
- Cyrus B. Meher-Homji, Eric Prisell: Pioneering Turbojet Developments of Dr. Hans Von Ohain — From the HeS 1 to the HeS 011 . In: Journal of Engineering for Gas Turbines and Power . tape 122 , no. 2 . ASME , 2000, pp. 191–201 , doi : 10.1115 / 1.483194 (English, asme.org [PDF; 458 kB ; accessed on May 7, 2019]).
Web links
Individual evidence
- ↑ a b The jet age began in Göttingen: Hans von Ohain's 100th birthday. In: dlr.de. December 9, 2011, accessed April 28, 2019 .
- ^ Sir Frank Whittle : Gas Turbine Aero-Thermodynamics . With Special Reference to Aircraft Propulsion. 1st edition. Pergamon Press Ltd, Oxford 1981, ISBN 0-08-026719-X , pp. 103 (English, limited preview in Google Book Search [accessed on May 12, 2019]).
- ^ Aurel Stodola : Steam and gas turbines . With an appendix on the prospects for heat engines. 6th edition. Springer, Berlin / Heidelberg 1924, ISBN 978-3-642-50544-7 , p. 1010-1011 , doi : 10.1007 / 978-3-642-50854-7 ( limited preview in Google Book Search [accessed May 12, 2019]).
- ^ Claire Soares: Gas Turbines: A Handbook of Air, Land and Sea Applications . 2nd Edition. Elsevier, 2014, ISBN 978-0-12-410461-7 , pp. 42 (English, limited preview in Google Book Search [accessed April 28, 2019]).
- ^ Willy JG Bräunling: aircraft engines . Basics, aero-thermodynamics, ideal and real cycle processes, thermal turbo machines, components, emissions and systems. 3. Edition. Springer, Berlin 2009, ISBN 978-3-540-76368-0 , pp. 13 .
- ↑ a b c Antony Kay: German Jet Engine and Gas Turbine Development 1930-1945 . Airlife Publishing Ltd, Shrewsbury 2002, ISBN 1-84037-294-X , pp. 18 (English).
- ↑ Cyrus B. Meher-Homji: The Historical Evolution of Turbomachinery . In: Proceedings of the 29th Turbomachinery Symposium . Housten 2000, p. 281–322 (English, tamu.edu [PDF; 2.6 MB ]).
- ^ Willy JG Bräunling: aircraft engines . Basics, aero-thermodynamics, ideal and real cycle processes, thermal turbo machines, components, emissions and systems. 3. Edition. Springer, Berlin 2009, ISBN 978-3-540-76368-0 , pp. 14 .
- ↑ a b c Cyrus B. Meher-Homji, Eric Prisell: Pioneering Turbojet Developments of Dr. Hans Von Ohain — From the HeS 1 to the HeS 011 . In: Journal of Engineering for Gas Turbines and Power . tape 122 , no. 2 . ASME , 2000, pp. 191–201 , doi : 10.1115 / 1.483194 (English, asme.org [PDF; 458 kB ]).
- ↑ Antony Kay: German Jet Engine and Gas Turbine Development 1930–1945 . Airlife Publishing Ltd, Shrewsbury 2002, ISBN 1-84037-294-X , pp. 19 (English).
- ↑ a b c Antony Kay: German Jet Engine and Gas Turbine Development 1930-1945 . Airlife Publishing Ltd, Shrewsbury 2002, ISBN 1-84037-294-X , pp. 20 (English).
Remarks
- ↑ The sources contradict each other here: according to Bräunling (p. 13) the compressor consisted of only one radial stage, according to Kay (p. 18) and Meher-Homji, however, it consisted of an axial and a subsequent radial stage.