energia: Gas-turbine engine

Evidence: 100 • authority: 72

A gas turbine is a complete continuous-flow internal combustion engine in which air is compressed, fuel is burned in the compressed air, and the resulting hot gas expands through a turbine. The turbine drives the compressor and, depending on the design, may also produce thrust, shaft power, or both. The compressor, combustor, and turbine form the gas generator or core of the engine. Gas turbines operate on the Brayton cycle and are used in aircraft propulsion, electric power generation, marine propulsion, industrial machinery, pumps, gas compressors, and some land vehicles. In aircraft, the same basic engine core may be used in turbojets, turbofans, turboprops, and turboshafts. In industria…

Evidence: 70 • authority: 72

A jet engine is a type of reaction engine, discharging a fast-moving jet of heated gas (usually air) that generates thrust by jet propulsion. While this broad definition may include rocket, water jet, and hybrid propulsion, the term jet engine typically refers to an internal combustion air-breathing jet engine such as a turbojet, turbofan, ramjet, pulse jet, or scramjet. In general, jet engines are internal combustion engines. Air-breathing jet engines typically feature a rotating air compressor powered by a turbine, with the leftover power providing thrust through the propelling nozzle—this process is known as the Brayton thermodynamic cycle. Jet aircraft use such engines for long-distance…

Evidence: 70 • authority: 72

Evidence: 64 • authority: 72

An internal combustion engine (ICE or IC engine) is a heat engine in which 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 components of the engine. The force is typically applied to pistons (piston engine), turbine blades (gas turbine), a rotor (Wankel engine), or a nozzle (jet engine). This force moves the component over a distance. This process transforms chemical energy into kinetic energy which is used to propel, move or power whatever the engine i…

Evidence: 57 • authority: 92

Online characterisation of oxidative potential and reactive oxygen species of fresh and aged aircraft turbine and ship engine particulate emissions.. Anthropogenic particulate matter (PM) emissions from the transport sector are a major contributor to global air pollution and associated adverse health effects. While the health impacts of PM are well-documented, the specific chemical and physical properties driving its toxicity, such as oxidative potential (OP) remain poorly understood and quantified. This study investigates the OP activity of PM emissions from a small jet engine combustion chamber (using JP-8 fuel) and a marine diesel engine (using low sulfur Heavy Fuel Oil, LS-HFO, and Mari…

Evidence: 57 • authority: 72

Evidence: 51 • authority: 72

A gas engine is an internal combustion engine that runs on a fuel gas (a gaseous fuel), such as coal gas, producer gas, biogas, landfill gas, natural gas or hydrogen. In the United Kingdom and British English-speaking countries, the term is unambiguous. In the United States, due to the widespread use of "gas" as an abbreviation for gasoline (petrol), such an engine is sometimes called by a clarifying term, such as gaseous-fueled engine or natural gas engine. Generally in modern usage, the term gas engine refers to a heavy-duty industrial engine capable of running continuously at full load for periods approaching a high fraction of 8,760 hours per year, unlike a gasoline automobile engine, w…

Evidence: 51 • authority: 72

Evidence: 51 • authority: 88

Evidence: 51 • authority: 72

Evidence: 44 • authority: 80

GAS TURBINE ENGINE COMBUSTION Introduction

Evidence: 38 • authority: 88

GAS TURBINE ENGINE INLET FLOW DISTORTION GUIDELINES. <div class="section abstract"> <div class="htmlview paragraph">The turbine-engine inlet flow distortion methodology addressed in this document applies only to the effects of inlet total-pressure distortion. Practices employed to quantify these effects are developing and therefore, periodic updates are anticipated. The effects of other forms of distortion on flow stability and performance and of any distortion on aeroelastic stability are not addressed.</div> <div class="htmlview paragraph">The guidelines can be used as necessary to create a development method to minimize the risk of inlet/engine compatibility problems. The degree to which…