| Revision as of 06:48, 10 September 2011 editPetebutt (talk | contribs)Autopatrolled, Extended confirmed users, Pending changes reviewers121,204 edits →Design and development← Previous edit | Revision as of 06:44, 3 November 2011 edit undoPetebutt (talk | contribs)Autopatrolled, Extended confirmed users, Pending changes reviewers121,204 editsNo edit summaryNext edit → | ||
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| {{Unreferenced|date=December 2009}} | {{Unreferenced|date=December 2009}} | ||
| __NOTOC__ | |||
| <!-- This article is a part of ]. Please see ] for recommended layout. --> | <!-- This article is a part of ]. Please see ] for recommended layout. --> | ||
| {|{{Infobox Aircraft Begin | |||
| |name=Hispano-Suiza 12Z | |||
| |image= | |||
| |size= | |||
| |alt= | |||
| |caption= | |||
| }}{{Infobox Aircraft Engine | |||
| ⚫ | |type =V-12 liquid-cooled piston engine | ||
| <!-- The type of engine, eg: Air-cooled rotary, High-bypass turbofan --> | |||
| |national origin =] | |||
| <!-- The country where the engine was first manufactured. Use the main nation (ie. UK), not constituent country (England); don't use "EU". List collaborative programs of only 2 or 3 nations; for more than 3, use "Multi-national --> | |||
| |manufacturer =] | |||
| <!-- The firm which manufactured the engine. --> | |||
| |designer = | |||
| <!-- The person or persons who designed the engine. Only appropriate for single designers, not project leaders --> | |||
| |first run = | |||
| <!-- The date that the engine was first run. If this hasn't happened, skip this field - don't speculate. --> | |||
| |major applications = | |||
| * ] | |||
| * ] | |||
| * ] | |||
| <!-- aircraft (or other vehicles) that were powered by this engine --> | |||
| |produced = | |||
| <!-- Years in production (eg. 1970-1999) if still in active use but no longer built --> | |||
| |number built = | |||
| |program cost = | |||
| <!-- Total program cost --> | |||
| |unit cost = | |||
| <!-- Incremental or flyaway cost for military or retail price for commercial aircraft --> | |||
| |developed from =] | |||
| <!-- The engine which formed the basis for this engine --> | |||
| |variants with their own articles = | |||
| <!-- Variants OF this engine --> | |||
| }} | |||
| |} | |||
| The '''12Z''' was the final evolution of the series of ] V-12 ]s, which had just entered production when ] fell to the ]s during ]. A small number were produced during the war but the German occupation government would not allow full-scale production to start. After the war small numbers were built to equip new designs, but the rapid introduction of the ] ended further development. | The '''12Z''' was the final evolution of the series of ] V-12 ]s, which had just entered production when ] fell to the ]s during ]. A small number were produced during the war but the German occupation government would not allow full-scale production to start. After the war small numbers were built to equip new designs, but the rapid introduction of the ] ended further development. | ||
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| * ] | * ] | ||
| ==Specifications (12Z- |
==Specifications (12Z-1)== | ||
| {{pistonspecs| | |||
| {{Pistonspecs | |||
| <!-- If you do not understand how to use this template, please ask at ] --> | |||
| <!-- Please include units where appropriate (main comes first, alt in parentheses). If data are missing, leave the parameter blank (do not delete it). For additional lines, end your alt units with </li> and start a new, fully |
<!-- Please include units where appropriate (main comes first, alt in parentheses). If data are missing, leave the parameter blank (do not delete it). For additional lines, end your alt units with )</li> and start a new, fully formatted line with <li> --> | ||
| |ref=<ref name="AEotW46">{{cite book|last=Wilkinson|first=Paul H.|title=Aircraft Engines of the World 1946|publisher=Sir Isaac Pitman & Sons Ltd.|location=London|date=1946|edition=revised 3rd}}</ref> | |||
| ⚫ | |type=12 |
||
| |type=V-12 60° liquid-cooled, geareed drive supercharged four stroke piston engine | |||
| |bore=150 mm (5.91 in) | |||
| | |
|bore=150mm (5.9in) | ||
| |stroke=170mm (6.69in) | |||
| |displacement=36.05 |
|displacement=36.05 litres (2,199.9in³) | ||
| |length= | |||
| |length=2,384mm (93.8in) | |||
| |diameter= | |diameter= | ||
| |width= | |width=744mm (29.3in) | ||
| |height= | |height=1,074mm (42.3in) | ||
| |weight= |
|weight=620kg (1,367lb) | ||
| |valvetrain=Two intake and two ]-cooled exhaust valves per cylinder actuated by dual ]s | |valvetrain=Two intake and two ]-cooled exhaust valves per cylinder actuated by dual ]s | ||
| |supercharger=Gear-driven single-stage |
|supercharger=Gear-driven single-stage two-speed ] with automatic boost control - ratios 6.36:1 and 9.38:1 | ||
| |turbocharger= | |turbocharger= | ||
| |fuelsystem=Direct fuel injection @ 40kg/cm² (570psi) 2x Lavalette P511-AS2 6-plunger injection pumps with 1x Lavalette KFD injector per cylinder | |||
| |fuelsystem= | |||
| |fueltype=100/130-] gasoline | |fueltype=100/130-] gasoline | ||
| |oilsystem=Dry sump, pressure feed @ 5kg/cm² (70psi), 20.5 centistokes (100S.U. secs) viscosity oil | |||
| |oilsystem= | |||
| |coolingsystem= |
|coolingsystem=Ethylene Glycol/water mix | ||
| |power=<br> | |power=<br> | ||
| *Take-off - 1,342kW (1,800hp) @ 1,150mm (45.3in)Hg boost @ 2,800rpm | |||
| *970 kW (1,300 hp) at 2,650 rpm for takeoff | |||
| *1, |
*Military, low - 1,193kW (1,600hp) @ 2,500m (8,200ft) @ 2,800rpm | ||
| *Military, high - 984kW (1,320hp) @ 8,000m (26,200ft) @ 2,800rpm | |||
| ⚫ | |specpower= |
||
| *Cruising, low - 1,193kW (900hp) @ 3,000m (9,800ft) @ 2,100rpm | |||
| ⚫ | |compression= |
||
| *Cruising, high - 1,193kW (900hp) @ 5,600m (18,400ft) @ 2,100rpm | |||
| ⚫ | |specpower=@ take-off power - 37.22kW/l (0.818hp/in³) | ||
| ⚫ | |compression=7.0:1 | ||
| |fuelcon= | |fuelcon= | ||
| |specfuelcon=0. |
|specfuelcon= 0.16kg/kW/hr (0.48lb/hp/hr) | ||
| |oilcon= | |oilcon=0.006 kg/kW/hr (0.018lb/hp/hr) | ||
| |power/weight= |
|power/weight=@take-off power - 2.16kW/kg (1.32hp/lb) | ||
| |designer= | |||
| |reduction_gear=Spur reduction gear ratio 0.6:1 | |||
| |general_other=Hollow propeller shaft to accomodate a cannon barrel | |||
| |components_other=Air Equipment 1525 compressed gas starting system | |||
| |performance_other=B.M.E.P. (Brake mean effective pressure) 16.3 kg/cm² (232psi) | |||
| }} | }} | ||
| ==See also== | ==See also== | ||
| *] | *] | ||
| ==References== | |||
| {{reflist}} | |||
| {{Hispano-Suiza aeroengines}} | {{Hispano-Suiza aeroengines}} | ||
Revision as of 06:44, 3 November 2011
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| Hispano-Suiza 12Z | |
|---|---|
| Type | V-12 liquid-cooled piston engine |
| National origin | France |
| Manufacturer | Hispano-Suiza |
| Major applications | * Ikarus S-49C |
| Developed from | Hispano-Suiza 12Y |
The 12Z was the final evolution of the series of Hispano-Suiza V-12 aircraft engines, which had just entered production when France fell to the Germans during World War II. A small number were produced during the war but the German occupation government would not allow full-scale production to start. After the war small numbers were built to equip new designs, but the rapid introduction of the jet engine ended further development.
Design and development
The 12Z differed from the earlier 12Y primarily in the use of four valves per cylinder operated by dual overhead cams. This gave the cylinders considerably better volumetric efficiency and faster operation, raising the RPM from 2,400 to 2,700. The engine was also designed to run only on 100 octane fuel (instead of 87, which was common at that point) which allowed the compression ratio to rise from the 12Y's 5.8:1 to the 12Z's 6.75:1. These changes raised the power from 1,000 to 1,300 hp (750 to 970 kW) at sea level. Unfortunately the engine continued to use a single-stage, single-speed supercharger and therefore lacked the all-altitude performance of German and British designs. But tuning the supercharger for a different critical altitude improved high-altitude performance considerably, delivering 1,500 hp (1,120 kW) at 21,000 ft (6,400 m) as opposed to 930 hp (690 kW) at 2,950 ft (900 m) for the 12Y.
Small prototype runs started in 1939, and were fitted to the French Armée de l'Air's front-line fighter aircraft, the M.S.410 and D.520, creating the M.S.450 and D.524 respectively. Production of the main model, the 12Z-17, was just starting at the time of the armistice. Production was undertaken in Hispano-Suiza's Spanish factories, but these engines had many problems and were never used in any numbers.
After the war a new version tuned to operate with 92 octane fuel, as opposed to the -17's 100/130, was built in limited numbers as the 12Z-89. Compression ratio was raised slightly to 7:1, but with the lower grade fuel the power dropped slightly to 1,280 hp (950 kW) at 2,600 rpm (1,479 hp (1,100 kW) maximum take-off). These engines apparently had the same sorts of reliability issues as the earlier -17's made in Spain, and the type never entered production.
Variants
- Hispano-Suiza 12Z-1
- The initial version of the engine used for develpment
- Hispano-Suiza 12Z-17
- development peak at time of the Fall of France in May 1940
- Hispano-Suiza 12Z-89
- post-war development,not successful.
Applications
Specifications (12Z-1)
Data from
General characteristics
- Type: V-12 60° liquid-cooled, geareed drive supercharged four stroke piston engine
- Bore: 150mm (5.9in)
- Stroke: 170mm (6.69in)
- Displacement: 36.05 litres (2,199.9in³)
- Length: 2,384mm (93.8in)
- Width: 744mm (29.3in)
- Height: 1,074mm (42.3in)
- Dry weight: 620kg (1,367lb)
- Hollow propeller shaft to accomodate a cannon barrel
Components
- Valvetrain: Two intake and two sodium-cooled exhaust valves per cylinder actuated by dual overhead camshafts
- Supercharger: Gear-driven single-stage two-speed centrifugal type supercharger with automatic boost control - ratios 6.36:1 and 9.38:1
- Fuel system: Direct fuel injection @ 40kg/cm² (570psi) 2x Lavalette P511-AS2 6-plunger injection pumps with 1x Lavalette KFD injector per cylinder
- Fuel type: 100/130-octane rating gasoline
- Oil system: Dry sump, pressure feed @ 5kg/cm² (70psi), 20.5 centistokes (100S.U. secs) viscosity oil
- Cooling system: Ethylene Glycol/water mix
- Reduction gear: Spur reduction gear ratio 0.6:1
- Air Equipment 1525 compressed gas starting system
Performance
- Power output:
- Take-off - 1,342kW (1,800hp) @ 1,150mm (45.3in)Hg boost @ 2,800rpm
- Military, low - 1,193kW (1,600hp) @ 2,500m (8,200ft) @ 2,800rpm
- Military, high - 984kW (1,320hp) @ 8,000m (26,200ft) @ 2,800rpm
- Cruising, low - 1,193kW (900hp) @ 3,000m (9,800ft) @ 2,100rpm
- Cruising, high - 1,193kW (900hp) @ 5,600m (18,400ft) @ 2,100rpm
- Specific power: @ take-off power - 37.22kW/l (0.818hp/in³)
- Compression ratio: 7.0:1
- Specific fuel consumption: 0.16kg/kW/hr (0.48lb/hp/hr)
- Oil consumption: 0.006 kg/kW/hr (0.018lb/hp/hr)
- Power-to-weight ratio: @take-off power - 2.16kW/kg (1.32hp/lb)
- B.M.E.P. (Brake mean effective pressure) 16.3 kg/cm² (232psi)
See also
References
- Wilkinson, Paul H. (1946). Aircraft Engines of the World 1946 (revised 3rd ed.). London: Sir Isaac Pitman & Sons Ltd.
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