Wikipedia:WikiProject Aircraft/Engines/page content

Lead

For general advice on lead section contents see Wikipedia:Lead section. The lead of an aero engine article should contain the following basic information when known:

• Name/designation.
• Manufacturer.
• Nationality.
• Type (e.g. turboprop, radial engine).
• Timeframe (e.g. World War II or 'produced between 19XX and 19XX'.
• Number built.
• Major aircraft type applications.

Citations are not required in the lead section if the facts are cited elsewhere in the article text and are unlikely to be challenged (see WP:LEADCITE).

Applications

It is usual to list all known aircraft type applications from reliable sources (including testbeds) for aero engines. For ship or land vehicle applications a sub-header is often used for clarity, i.e. Other applications or Alternative uses. Larger lists can be formatted into columns using Template:Columns-list to save page length and white space. It is advisable to add a note or cite any unusual or contentious applications that may be questioned by other editors.

Survivors/Engines on display sections

• The survivors section relates to airworthy, older, out of production engines, that are currently powering vintage aircraft types.
• Engines on display should include museum exhibits that are accessible to the public.

See also section

See also sections are completed using the Aircontent template. Please include the list of aircraft engines for every type. For 'comparable' engines it is desirable to limit the number of entries by selecting the closest similar types. Some useful parameters are era, layout, number of cylinders, engine displacement and power/thrust rating.

Reciprocating (piston) engines

General characteristics

• Type: (example: Seven-cylinder, supercharged, air-cooled radial piston engine)
• Bore: x in (x mm)
• Stroke: x in (x mm)
• Displacement: x in³ (x L)
• Length: x in (x mm)
• Diameter: x in (x mm) Note:Usually only used for radial and rotary engines, left blank in others
• Width: x in (x mm)
• Height: x in (x mm)
• Dry weight: x lb (x kg)
• Designer: (example:Frank Halford) Note:Usually reserved for single designers or the head of a small team

Components

• Valvetrain: (example: Two pushrod-actuated valves per cylinder with sodium-cooled exhaust valve, overhead camshaft-actuated, two intake and two exhaust valves per cylinder, sodium-cooled exhaust valve stems)
• Supercharger: (example: Two-speed two-stage, boost pressure automatically linked to the throttle, water-air aftercooler installed between the second stage and the engine)
• Fuel system: (example: Twin-choke updraft carburetor with automatic mixture control) Note:Alternative spellings of updraught and carburettor for British/Commonwealth engines
• Fuel type: (example: Avgas)
• Oil system: (example: Dry sump with one pressure pump and two scavenge pumps)
• Cooling system: (example: 70% water and 30% ethylene glycol coolant mixture) or simply 'Air-cooled'
• Reduction gear: (Example: 0.5:1) Note:Often simply 'Direct-drive' and noting the direction of rotation i.e. 'Left-hand tractor'

Performance

• Power output: x hp (x kW) at rpm for takeoff at sea level; x hp (x kW) at rpm for cruise at x ft (x m)
• Specific power: x hp/in³ (x kW/L)
• Compression ratio: (Example: 6:1)
• Fuel consumption: x US (or Imp) gal/h (x L/h) at economical cruise
• Specific fuel consumption: (acceptable alternative to fuel consumption)
• Oil consumption: x US (or Imp) gal/h (x L/h)
• Power-to-weight ratio: x hp/lb (x kW/kg)

Explanation of pistonspecs template parameters

• |type= Engine in a nutshell, #-cylinder turbo/supercharged air/liquid-cooled inline/rotary/V-# piston aircraft engine
• |designer= Who
• |bore= Diameter of each cylinder, in (mm)
• |stroke= Distance the piston travels inside the cylinder, in (mm)
• |displacement= Total volume of the engine, in³ (L)
• |length= Length of the engine, in (mm)
• |diameter= Diameter or width of the engine, in (mm)
• |width= Width of the engine, in (mm)
• |height= Height of the engine, in (mm)
• |weight= Dry weight of the engine (without oil, coolant, etc.), lb (kg)
• |valvetrain= Description of valves, including number of intake/exhaust valves per cylinder and valve operation (camshaft/pushrod, OHV/OHC), for example two pushrod-actuated valves per cylinder with sodium-cooled exhaust valve or overhead camshaft-actuated, two intake and two exhaust valves per cylinder, sodium-cooled exhaust valve stems
• |supercharger= Description of the supercharger, leave blank if not installed, for example two-speed two-stage, boost pressure automatically linked to the throttle, water-air aftercooler installed between the second stage and the engine
• |turbocharger= Description of the turbocharger, leave blank if not installed.
• |fuelsystem= Description of the fuel system (carbutered/fuel injected, etc.), for example twin-choke updraft carburetor with automatic mixture control
• |fueltype= Fuel type, octane rating
• |oilsystem= Description of the oil system, for example dry sump with one pressure pump and two scavenge pumps
• |coolingsystem= Description of the cooling system, for example 70% water and 30% ethylene glycol coolant mixture, pressurized. At the very least say if the engine was air- or liquid-cooled.
• |reduction_gear If there's one, give the ratio or otherwise describe it
• |power= Power output, hp (kW) at # rpm
• |specpower= Specific power, power output divided by engine displacement; hp/in³ or kW/l
• |compression= Compression ratio, #:1
• |fuelcon= Fuel consumption, US gal/h (L/h) or lb/h (kg/h)
• |specfuelcon= Specific fuel consumption lb/(hp·h) (kg/(kW·h))
• |oilcon= Oil consumption US gal/h (L/h) or lb/h (kg/h)
• |power/weight= Power-to-weight ratio, calculated by dividing engine power by engine weight, hp/lb (kW/kg)

Gas turbine engines

General characteristics

• Type: (examples: turbofan, turbojet)
• Length: in ( mm)
• Diameter: in ( mm)
• Dry weight: lb ( kg)

Components

• Compressor: (example: Single-stage dual-entry centrifugal compressor with two-sided impeller; or axial compressor)
• Combustors: (example: 10 flow combustion chambers with igniter plugs in chambers 3 and 10)
• Turbine: (example: Single-stage axial flow)
• Fuel type: (example: Avtur)
• Oil system: US gal (L) capacity, circulation rate US gal/h (L/h), maximum inverted flying time

Performance

• Maximum thrust: lbf (kN) at rpm for takeoff; lbf (kN) at rpm for cruise; lbf (kN) at rpm at idle.
• Air mass flow: lb/s (kg/s)
• Turbine inlet temperature: °F (°C)
• Fuel consumption: lb/h (kg/h) at maximum power; lb/h (kg/h) at cruise power; lb/h (kg/h) at idle
• Specific fuel consumption: (acceptable alternative to fuel consumption)

Explanation of jetspecs template parameters

• |type= Engine in a nutshell, afterburning turbofan/turbojet/turboshaft/turboprop engine
• |length= Length of the engine, in (mm)
• |diameter= Diameter or width of the engine, in (mm)
• |weight= Dry weight of the engine (without oil, coolant, etc.), lb (kg)
• |compressor= Description of the compressor (number of stages, high/low pressure stages, number of blades, etc.), for example single-stage dual-entry centrifugal compressor with two-sided impeller (axial compressor should also be wiki-linked). At the very least specify if it is an axial or a centrifugal compressor.
• |combustion= Description of the combustion chambers, for example 10 flow combustion chambers with igniter plugs in chambers 3 and 10
• |turbine= Description of the turbine, for example single-stage axial flow with 54 blades
• |fueltype= Fuel type, for example aviation kerosene with 1% lubricating oil
• |oilsystem= Description of the oil system, US gal (L) capacity, oil circulation rate US gal/h (L/h), maximum inverted flying time, etc.
• |power= Power (for gas-turbine engines), shp (kW)
• |thrust= Thrust, lbf (kN) at # rpm, specify if afterburning or non-afterburning.
• |compression= Overall pressure ratio, #:1
• |bypass= Bypass ratio
• |aircon= Air consumption, lb/s (kg/s)
• |turbinetemp= Turbine inlet temperature, °F (°C)
• |fuelcon= Fuel consumption, US gal/h (L/h) or lb/h (kg/h)
• |specfuelcon= Specific fuel consumption lb/(lbf·h) (kg/(kN·h))
• |thrust/weight= Thrust-to-weight ratio, calculated by dividing engine thrust by engine weight, lbf thrust divided by lb weight is unitless. Metric kN/kg is the same except multiplied by 9.8.
• |Power/weight= Power-to-weight ratio (for gas-turbine engines), calculated by dividing engine power by engine weight, shp/lb (kW/kg)