Ad
related to: combustion chamber gas turbine engine for sale
Search results
Results From The WOW.Com Content Network
A combustor is a component or area of a gas turbine, ramjet, or scramjet engine where combustion takes place. It is also known as a burner, burner can, combustion chamber or flame holder. In a gas turbine engine, the combustor or combustion chamber is fed high-pressure air by the compression system. The combustor then heats this air at constant ...
The combustion chamber in gas turbines and jet engines (including ramjets and scramjets) is called the combustor. The combustor is fed with high pressure air by the compression system, adds fuel and burns the mix and feeds the hot, high pressure exhaust into the turbine components of the engine or out the exhaust nozzle.
Diagram of a typical gas turbine jet engine Frank Whittle Hans von Ohain. The turbojet is an airbreathing jet engine which is typically used in aircraft. It consists of a gas turbine with a propelling nozzle. The gas turbine has an air inlet which includes inlet guide vanes, a compressor, a combustion chamber, and a turbine (that drives the ...
The 1906 machine was the last large gas turbine built by the Société Anonyme des Turbomoteurs. The society ceased all work on gas turbines after the death of Rene Armengaud in 1909. [6] The combustion chamber of the 1906 gas turbine was successfully developed, and licensed by the society, for use in naval torpedoes. [6]
A gas turbine or gas turbine engine is a type of continuous flow internal combustion engine. [1] The main parts common to all gas turbine engines form the power-producing part (known as the gas generator or core) and are, in the direction of flow: a rotating gas compressor; a combustor; a compressor-driving turbine.
The turbines are concentric with the combustion chamber, reducing overall length. In most aircraft installations the PT6 is mounted so that the intake end of the engine is towards the rear of the aircraft, leading to it being known by many as the "back-to-front" engine. [ 4 ]
The engine featured a single-stage fan, a three-stage low-pressure compressor, and an eleven-stage high-pressure compressor coupled to a two-stage high-pressure turbine and four-stage low-pressure turbine. The JT9D-3, the earliest certified version of the engine, weighed 8,470 lb (3,840 kg) and produced 43,500 lbf (193 kN) thrust. [7]
Initially, the first engines developed (GT-300 and 302) did not have a regenerator, but adding regeneration to recapture heat from the exhaust gases was found to reduce fuel consumption by 1 ⁄ 2 for the second-generation GT-304, so subsequent generations of GM Whirlfire gas turbine engines incorporated a regenerator.