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Turbomeca Gabizo
The TURBOMECA GABIZO was a small turbojet engine produced by Turbomeca
Turbomeca
from the 1950s. The components were designed to take the stresses of high-speed fighter aircraft with some variants featuring afterburner
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Auxiliary Power Unit
An AUXILIARY POWER UNIT (APU) is a device on a vehicle that provides energy for functions other than propulsion . They are commonly found on large aircraft and naval ships as well as some large land vehicles. Aircraft
Aircraft
APUs generally produce 115 V alternating current (AC) at 400 Hz (rather than 50/60 Hz in mains supply), to run the electrical systems of the aircraft; others can produce 28 V direct current (DC). APUs can provide power through single- or three-phase systems
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MTR MTR390
Mass Transit Railway (MTR) TRADITIONAL CHINESE 港鐵 SIMPLIFIED CHINESE 港铁 HANYU PINYIN Gǎngtiě CANTONESE YALE Góngtit LITERAL MEANING " Hong Kong
Hong Kong
railway" TRANSCRIPTIONS STANDARD MANDARIN HANYU PINYIN Gǎngtiě IPA HAKKA ROMANIZATION Kóng-Thiet YUE: CANTONESE YALE ROMANIZATION Góngtit IPA JYUTPING Gong2tit3The MASS TRANSIT RAILWAY (MTR; Chinese : 港鐵; Cantonese
Cantonese
Yale : Góngtit) is a major public transport network serving Hong Kong
Hong Kong
. Operated by the MTR Corporation
MTR Corporation
Limited (MTRCL), it consists of heavy rail , light rail , and feeder bus service centred on an 11-line rapid transit network serving the urbanised areas of Hong Kong
Hong Kong
Island , Kowloon
Kowloon
, the New Territories
New Territories

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Aircraft Engine
An AIRCRAFT ENGINE is the component of the propulsion system for an aircraft that generates mechanical power . Aircraft
Aircraft
engines are almost always either lightweight piston engines or gas turbines , except for small multicopter UAVs which are almost always electric aircraft
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Special
SPECIAL or SPECIALS may refer to: CONTENTS * 1 Music * 2 Film and television * 3 Other uses * 4 See also MUSIC * Special (album) , a 1992 album by Vesta Williams * "Special" (Garbage song) , 1998 * "Special" (Mew song) , 2005 * "Special" (Stephen Lynch song) , 2000 * The Specials
The Specials
, a British band * "Special", a song by Violent Femmes on The Blind Leading the Naked * "Special", a song on
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Rolls-Royce Turbomeca Adour
The ROLLS-ROYCE TURBOMECA ADOUR is a two-shaft low bypass turbofan aircraft engine developed by Rolls-Royce Turbomeca Limited
Rolls-Royce Turbomeca Limited
, a joint subsidiary of Rolls-Royce (UK) and Turbomeca
Turbomeca
(France). The engine is named after the Adour
Adour
, a river in south western France. CONTENTS * 1 History * 2 Variants * 2.1 Reheated (Afterburning) * 2.2 Dry (Non-afterburning) * 2.3 Higher bypass * 3 Applications * 3.1 Licence-built * 4 Specifications ( Adour
Adour
Mk 106) * 4.1 General characteristics * 4.2 Components * 4.3 Performance * 5 See also * 6 References * 7 External links HISTORYThe Adour
Adour
is a turbofan engine developed primarily to power the Anglo-French SEPECAT Jaguar
SEPECAT Jaguar
fighter-bomber, achieving its first successful test run in 1968
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MTU Turbomeca Rolls-Royce
MTU TURBOMECA ROLLS-ROYCE GMBH (MTR) is a joint venture among three European aero-engine manufacturers, MTU Aero Engines , Turbomeca
Turbomeca
and Rolls-Royce
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Hindustan Aeronautics Limited
HINDUSTAN AERONAUTICS LIMITED (HAL) is an Indian state-owned aerospace and defence company based in Bangalore, Karnataka
Karnataka
. It is governed under the management of the Indian Ministry of Defence . The government-owned corporation is primarily involved in the operations of the aerospace industry. These include manufacturing and assembly of aircraft, navigation and related communication equipment and airports operation. HAL built the first military aircraft in South Asia. It is currently involved in the design, fabrication and assembly of aircraft , jet engines , helicopters and their spare parts. It has several facilities spread across India. The locations where the manufacturing plants are operated by HAL include Nasik , Korwa , Kanpur
Kanpur
, Koraput , Lucknow
Lucknow
, Bangalore
Bangalore
and Hyderabad
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Turboshaft
A TURBOSHAFT engine is a form of gas turbine which is optimized to produce shaft power rather than jet thrust . In concept, turboshaft engines are very similar to turbojets , with additional turbine expansion to extract heat energy from the exhaust and convert it into output shaft power. They are even more similar to turboprops , with only minor differences, and a single engine is often sold in both forms. Turboshaft
Turboshaft
engines are commonly used in applications that require a sustained high power output, high reliability, small size, and light weight. These include helicopters , auxiliary power units , boats and ships , tanks , hovercraft , and stationary equipment. CONTENTS * 1 Overview * 2 History * 3 See also * 4 References * 5 External links OVERVIEWA turboshaft engine may be made up of two major parts assemblies: the 'gas generator' and the 'power section'
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Turboprop
A TURBOPROP engine is a turbine engine that drives an aircraft propeller . In contrast to a turbojet , the engine's exhaust gases do not contain enough energy to create significant thrust, since almost all of the engine's power is used to drive the propeller. In its simplest form a turboprop consists of an intake, compressor , combustor , turbine , and a propelling nozzle . Air is drawn into the intake and compressed by the compressor. Fuel is then added to the compressed air in the combustor, where the fuel-air mixture then combusts . The hot combustion gases expand through the turbine. Some of the power generated by the turbine is used to drive the compressor. The rest is transmitted through the reduction gearing to the propeller. Further expansion of the gases occurs in the propelling nozzle, where the gases exhaust to atmospheric pressure. The propelling nozzle provides a relatively small proportion of the thrust generated by a turboprop
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Turbofan
The TURBOFAN or FANJET is a type of airbreathing jet engine that is widely used in aircraft propulsion. The word "turbofan" is a portmanteau of "turbine" and "fan": the turbo portion refers to a gas turbine engine which achieves mechanical energy from combustion, and the fan, a ducted fan that uses the mechanical energy from the gas turbine to accelerate air rearwards. Thus, whereas all the air taken in by a turbojet passes through the turbine (through the combustion chamber), in a turbofan some of that air bypasses the turbine. A turbofan thus can be thought of as a turbojet being used to drive a ducted fan, with both of those contributing to the thrust. The ratio of the mass-flow of air bypassing the engine core compared to the mass-flow of air passing through the core is referred to as the bypass ratio
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Turbojet
The TURBOJET is an airbreathing jet engine , usually used in aircraft. It consists of a gas turbine with a propelling nozzle . The gas turbine has an air inlet, a compressor, a combustion chamber, and a turbine (that drives the compressor). The compressed air from the compressor is heated by the fuel in the combustion chamber and then allowed to expand through the turbine. The turbine exhaust is then expanded in the propelling nozzle where it is accelerated to high speed to provide thrust. Two engineers, Frank Whittle in the United Kingdom and Hans von Ohain in Germany
Germany
, developed the concept independently into practical engines during the late 1930s. Turbojets have been replaced in slower aircraft by turboprops because they have better range-specific fuel consumption . At medium speeds, where the propeller is no longer efficient, turboprops have been replaced by turbofans
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Thrust-to-weight Ratio
THRUST-TO-WEIGHT RATIO is a dimensionless ratio of thrust to weight of a rocket , jet engine , propeller engine, or a vehicle propelled by such an engine that indicates the performance of the engine or vehicle. The instantaneous thrust-to-weight ratio of a vehicle varies continually during operation due to progressive consumption of fuel or propellant and in some cases a gravity gradient. The thrust-to-weight ratio based on initial thrust and weight is often published and used as a figure of merit for quantitative comparison of the initial performance of vehicles. CONTENTS * 1 Calculation * 2 Aircraft * 2.1 Propeller-driven aircraft * 3 Rockets * 4 Examples * 4.1 Aircraft * 4.2 Jet and rocket engines * 4.3 Fighter aircraft * 5 See also * 6 References * 6.1 Notes * 7 External links CALCULATIONThe thrust-to-weight ratio can be calculated by dividing the thrust (in SI units – in newtons ) by the weight (in newtons) of the engine or vehicle
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International Standard Book Number
The INTERNATIONAL STANDARD BOOK NUMBER (ISBN) is a unique numeric commercial book identifier. An ISBN is assigned to each edition and variation (except reprintings) of a book. For example, an e-book , a paperback and a hardcover edition of the same book would each have a different ISBN. The ISBN is 13 digits long if assigned on or after 1 January 2007, and 10 digits long if assigned before 2007. The method of assigning an ISBN is nation-based and varies from country to country, often depending on how large the publishing industry is within a country. The initial ISBN configuration of recognition was generated in 1967 based upon the 9-digit STANDARD BOOK NUMBERING (SBN) created in 1966. The 10-digit ISBN format was developed by the International Organization for Standardization (ISO) and was published in 1970 as international standard ISO 2108 (the SBN code can be converted to a ten digit ISBN by prefixing it with a zero)
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Snecma
SAFRAN AIRCRAFT ENGINES (previously SNECMA) is a French aerospace engine manufacturer headquartered in Courcouronnes , France. It is among the top suppliers in the industry, with end-to-end expertise from design to production of high-performance aircraft engines for commercial and military aircraft as well as rocket engines for launch vehicles and satellites . It also offers a complete range of engine support services to airlines, armed forces and other operators. Some of its notable past developments, alone or in partnership, include the M88 for the Rafale , Olympus 593 for the Concorde , CFM56 /CFM-LEAP for single-aisle airliners, and the Vulcain engines for the Ariane 5 . It has 15,700 employees working at 35 production sites, offices, and MRO facilities worldwide. It plows a significant portion of its sales back into research and development, filing an average of nearly 500 patents each year
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Thrust Specific Fuel Consumption
THRUST SPECIFIC FUEL CONSUMPTION (TSFC) is an engineering term that is used to describe the fuel efficiency of an engine design with respect to thrust output. TSFC may also be thought of as fuel consumption (grams/second) per unit of thrust (kilonewtons, or kN). It is thus thrust-specific, meaning that the fuel consumption is divided by the thrust. TSFC or SFC for thrust engines (e.g. turbojets , turbofans , ramjets , rocket engines , etc.) is the mass of fuel needed to provide the net thrust for a given period e.g. lb/(h·lbf) (pounds of fuel per hour-pound of thrust) or g/(s·kN) (grams of fuel per second-kilonewton). Mass of fuel is used rather than volume (gallons or litres) for the fuel measure since it is independent of temperature
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