In a Front-engine, rear-wheel-drive layout what type of engine is a heat engine where the combustion of a fuel occurs with an oxidizer (usually air) in a combustion chamber that is an integral part of the working fluid flow circuit?
An internal combustion engine
Front-engine, rear-wheel-drive layout
In automotive design, an FR, or front-engine, rear-wheel-drive layout is one where the engine is located at the front of the vehicle and driven wheels are located at the rear.
 This was the traditional automobile layout for most of the 20th century.
 Modern designs commonly use the front-engine, front-wheel-drive layout (FF).
Internal combustion engine
An internal combustion engine (ICE) is a heat engine where the combustion of a fuel occurs with an oxidizer (usually air) in a combustion chamber that is an integral part of the working fluid flow circuit.
 In an internal combustion engine, the expansion of the high-temperature and high-pressure gases produced by combustion applies direct force to some component of the engine.
 The force is applied typically to pistons, turbine blades, rotor or a nozzle.
 This force moves the component over a distance, transforming chemical energy into useful mechanical energy.
Combined cycle
In electric power generation a combined cycle is an assembly of heat engines that work in tandem from the same source of heat, converting it into mechanical energy, which in turn usually drives electrical generators.
 The principle is that after completing its cycle (in the first engine), the temperature of the working fluid engine is still high enough that a second subsequent heat engine may extract energy from the waste heat that the first engine produced.
 By combining these multiple streams of work upon a single mechanical shaft turning an electric generator, the overall net efficiency of the system may be increased by 50–60%.
 That is, from an overall efficiency of say 34% (in a single cycle) to possibly an overall efficiency of 51% (in a mechanical combination of two cycles) in net Carnot thermodynamic efficiency.
 This can be done because heat engines are only able to use a portion of the energy their fuel generates (usually less than 50%).
 In an ordinary (non combined cycle) heat engine the remaining heat (e.g., hot exhaust fumes) from combustion is generally wasted. Combustion tap-off cycle
The combustion tap-off cycle is a power cycle of a bipropellant rocket engine.
 The cycle takes hot gases from the main combustion chamber of the rocket engine and routes them through engine turbopump turbines to pump fuel, then is exhausted.
 Since not all fuel flows through the main combustion chamber, the tap-off cycle is considered an open-cycle engine.
 The cycle is comparable to a gas-generator cycle engine with turbines driven by main combustion chamber exhaust rather than a gas-generator. Diesel engine
The diesel engine (also known as a compression-ignition or CI engine) and named after Rudolf Diesel, is an internal combustion engine in which ignition of the fuel which is injected into the combustion chamber is caused by the elevated temperature of the air in the cylinder due to mechanical compression (adiabatic compression).
 Diesel engines work by compressing only the air.
 This increases the air temperature inside the cylinder to such a high degree that atomised diesel fuel that is injected into the combustion chamber ignites spontaneously .
 This contrasts with spark-ignition engines such as a petrol engine (gasoline engine) or gas engine (using a gaseous fuel as opposed to petrol), which use a spark plug to ignite an air-fuel mixture.
 In diesel engines, glow plugs (combustion chamber pre-warmers) may be used to aid starting in cold weather, or when the engine uses a lower compression-ratio, or both.
 The original diesel engine operates on the "constant pressure" cycle of gradual combustion and produces no audible knock. External combustion engine
An external combustion engine (EC engine) is a heat engine where a working fluid, contained internally, is heated by combustion in an external source, through the engine wall or a heat exchanger.
 The fluid then, by expanding and acting on the mechanism of the engine, produces motion and usable work.
 The fluid is then cooled, compressed and reused (closed cycle), or (less commonly) dumped, and cool fluid pulled in (open cycle air engine). Pressure-fed engine
The pressure-fed engine is a class of rocket engine designs.
 A separate gas supply, usually helium, pressurizes the propellant tanks to force fuel and oxidizer to the combustion chamber.
 To maintain adequate flow, the tank pressures must exceed the combustion chamber pressure. Expander cycle
The expander cycle is a power cycle of a bipropellant rocket engine.
 In this cycle, the fuel is used to cool the engine's combustion chamber, picking up heat and changing phase.
 The heated, now gaseous, fuel then powers the turbine that drives the engine's fuel and oxidizer pumps before being injected into the combustion chamber and burned. Stirling engine
A Stirling engine is a heat engine that operates by cyclic compression and expansion of air or other gas (the "working fluid") at different temperatures, such that there is a net conversion of heat energy to mechanical work.
 More specifically, the Stirling engine is a closed-cycle regenerative heat engine with a permanently gaseous working fluid.
 "Closed-cycle", in this context, means a thermodynamic system in which the working fluid is permanently contained within the system, and "regenerative" describes the use of a specific type of internal heat exchanger and thermal store, known as the "regenerator".
 The inclusion of a regenerator differentiates the Stirling engine from other closed cycle hot air engines. XLR81
The Bell Aerosystems Company XLR81 (Model 8096) was an American liquid-propellant rocket engine, which was used on the Agena upper stage.
 It burned UDMH and RFNA fed by a turbopump in a fuel rich gas generator cycle.
 The turbopump had a single turbine with a gearbox to transmit power to the oxidizer and fuel pumps.
 The thrust chamber was all-aluminum, and regeneratively cooled by oxidizer flowing through gun-drilled passages in the combustion chamber and throat walls.
 The nozzle was a titanium radiatively cooled extension.
 The engine was mounted on an hydraulic actuated gimbal which enabled it thrust vectoring to control pitch and yaw.
 Engine thrust and mixture ratio were controlled by cavitating flow venturis on the gas generator flow circuit.
 Engine start was achieved by solid propellant start cartridge.