159:. In order to minimise the diameter the widest part of the annular combustor was placed in line with the smaller diameter axial entry to the impeller. At exit from the impeller the air flowed forwards, then turned through 180 degrees to flow rearward through the combustor. The flow was then turned radially inwards to enter the turbine. Although not as compact as the original design, the 3b was much simpler. The fuel was used to cool rear roller bearing, which also preheated the fuel.
152:. The compressed air flowed into an annular combustion chamber between the compressor and turbine, which made the engine longer. The first example was bench tested around March 1938, but did not reach the design thrust because a small compressor and combustor had been used to reduce the frontal area. Max Hahn, from Heinkel, applied May 31, 1939, for a US patent, granted Sept 16, 1941: 'Aircraft Power Plant', US2256198, with the von Ohain design.
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late in 1939. While successful, raising thrust just above 590 kp (1,300 lbf), weight increased from 360 to 420 kg. The diameter of the engines remained too large to directly substitute the planned HeS 30 (109-006) engines on the He 280 fighter, therefore the design was abandoned in
173:
A second engine was completed just after completion of the He 178 airframe, so it was decided to move directly to full flight tests. A short hop was made on 24 August during high-speed taxi tests, followed by full flight on 27 August, the first aircraft to fly solely under jet power. Testing
169:
prototypes. The flight tests were carried out in extreme secrecy, taking off and landing under propeller power, and only flying in the early morning before other workers had arrived. Testing proceeded smoothly, but the engine eventually burned out its turbine.
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manufacturers to try to start programs there. Mauch left his position in 1939 leaving Schelp in command. Schelp was not as concerned about where development was taking place, and immediately started funding
Heinkel to produce a more powerful engine.
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Hans Mauch later told von Ohain the RLM was in fact extremely impressed, but he was concerned that
Heinkel's airframe team did not have the knowledge to undertake engine development. Instead he and
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but converted to burn liquid fuel instead of hydrogen gas used in the HeS 1. The first HeS 3 design was generally similar to the HeS 1, using an 8-blade inducer and 16-blade
352:"Pioneering Turbojet Developments of Dr. Hans Von Ohain-From the HeS 1 to the HeS 011" Meher-Homji and Prisell, Transactions of the ASME, Vol. 122, April 2000
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on 27 August 1939. Although successful, the engine had too little thrust to be really useful, and work started on the more powerful
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website (the world's first jet pilot), inclusive rare videos (Heinkel He 178 & HeS 3 turbine) and audio commentaries
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officials in hopes of receiving funding for the development of a larger engine, but nothing seemed forthcoming.
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The engine was completed in early 1939, and was flight-tested under one of the remaining
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Pioneering
Turbojet Developments of Dr. Hans von Ohain — From the HeS 1 to the HeS 011
372:"A Performance Diagnosis of the 1939 Heinkel HE S3B Turbojet" C. Rodgers, GT2004-53014
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World
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An improved engine, the HeS 3b, had a 14-blade inducer and 16 blade
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The First Jet Pilot - The Story of German Test Pilot Erich
Warsitz
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14-blade axial inducer + 16-blade centrifugal flow compressor
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4.9 kN; 1,100 lbf (500 kp) at 11,600 rpm (at
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continued and in
November the aircraft was demonstrated to
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German Jet Engine and Gas
Turbine Development 1930–1945
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utilizing a straight-through flow combustion layout.
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33:A sectioned Heinkel HeS 3 Turbojet engine at the
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436:. Vol. 1. Ramsbury: The Crowood Press.
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434:Turbojet History and Development 1930–1960
144:The HeS 3 design was largely based on the
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465:Military Turbojet/Turbofan Specifications
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454:, Pen and Sword Books, England, 2009,
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398:(5th ed.). Stroud, UK: Sutton.
112:) was the world's first operational
136:as their first production design.
116:to power an aircraft. Designed by
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802:Centrifugal-flow turbojet engines
44:Centrifugal flow turbojet engine
233:Centrifugal flow turbojet engine
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282:12-blade radial inflow turbine
198:Work on a larger version, the
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185:secretly visited a number of
207:favour of the more compact
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239:1,480 mm (58 in)
65:Heinkel-Hirth Motorenwerke
251:360 kg (790 lb)
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807:Heinkel aircraft engines
432:Kay, Anthony L. (2007).
413:Kay, Anthony L. (2002).
245:930 mm (37 in)
110:Heinkel Strahltriebwerke
225:General characteristics
215:Specifications (HeS 3b)
812:1930s turbojet engines
394:Gunston, Bill (2006).
326:Overall pressure ratio
157:centrifugal compressor
150:centrifugal compressor
417:. The Crowood Press.
381:Kay 2007, pp. 171–174
336:12.6 kg/s (27.7 lb/s)
273:Reverse-flow annular
472:2011-10-02 at the
80:Major applications
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305:Performance
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293:Diesel fuel
262:Compressor:
249:Dry weight:
167:dive bomber
140:Development
796:Categories
341:References
286:Fuel type:
269:Combustors
256:Components
114:jet engine
71:First run
243:Diameter:
220:Data from
470:Archived
311:Maximum
289:Gasoline
781:HeS 011
278:Turbine
237:Length:
122:Heinkel
108:(HeS -
55:Germany
776:HeS 60
771:HeS 50
766:HeS 40
761:HeS 30
605:HM 515
600:HM 512
595:HM 508
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585:HM 504
580:HM 501
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19:HeS 3
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751:HeS 3
746:HeS 1
648:F-263
565:HM 60
537:Hirth
330:2.8:1
231:Type:
200:HeS 6
194:HeS 6
146:HeS 1
74:1939
41:Type
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560:HM 8
539:and
456:ISBN
438:ISBN
419:ISBN
400:ISBN
104:The
319:SSL
291:or
176:RLM
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