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Ishikawajima-Harima F3
The Ishikawajima-Harima Heavy Industries (IHI) F3 is a low bypass turbofan engine developed in Japan by Ishikawajima-Harima Heavy Industries for the Kawasaki T-4 jet trainer aircraft. The first prototype engine, the XF3, was manufactured in 1981 and first flew in the XT-4 in July 1985. About 550 have been built. Design and development Ishikawajima-Harima began developing a small turbofan engine in the late 1970s as a competitor for the new jet trainer aircraft being developed by Kawasaki Heavy Industries. The developmental engine was named the XF3, and it was selected over the SNECMA Turbomeca Larzac in 1982 to power the XT-4 trainer. The early developmental models of the engine produced of thrust, but later models (including the model selected for the XT-4) produced of thrust. The production engine was designated the F3-30 (alternatively, the F3-IHI-30), and it first flew in the XT-4 aircraft in 1985. Production of the qualified engine also began in 1985.Hamada, T., A ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Turbofan
The turbofan or fanjet is a type of airbreathing jet engine that is widely used in aircraft engine, 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 force air rearwards. Thus, whereas all the air taken in by a turbojet passes through the combustion chamber and turbines, in a turbofan some of that air bypasses these components. A turbofan thus can be thought of as a turbojet being used to drive a ducted fan, with both of these contributing to the thrust. The ratio of the mass-flow of air bypassing the engine core to the mass-flow of air passing through the core is referred to as the bypass ratio. The engine produces thrust through a combination of these two portions working together; engines that use more Propelling nozzle, jet thrust relative to fan thrust are ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
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 is an indicator of 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 a vehicle's initial performance. Calculation The thrust-to-weight ratio is calculated by dividing the thrust (in SI units – in newtons) by the weight (in newtons) of the engine or vehicle. Note that the thrust can also be measured in pound-force (lbf), provided the weight is measured in pounds (lb). Division using these two values still gives the numerically correct (dimensionless) thrust-to-weight ratio. For valid comparison of the initial ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
NPO Saturn AL-55
The NPO Saturn AL-55 is a high performance turbofan engine manufactured by NPO Saturn Russia, for powering advanced trainers, unmanned aerial vehicles (UAV) and light attack aircraft. A variant of the AL-55I powers the HAL HJT-36 Sitara Indian jet trainer. Design The design comprises five main features. It has a three-stage low pressure compressor, five stage high pressure chamber, an annular combustion chamber and a single stage high and low pressure turbines. In August 2005, the Russian export organization known as Rosoboronexport and India's Hindustan Aeronautics Limited (HAL) signed an agreement for the licensed production of up to 1,000 AL-55I engines. The agreement includes a firm order for 250 engines to be manufactured at HAL facilities in India, to power both HAL HJT-36 trainer and HAL HJT 39 combat trainer aircraft. Variants ;AL-55: :AL-55/I: A variant designed for licensed production in India. Applications * HAL HJT-36 Sitara * HAL HJT 39 * Mikoyan MiG-AT [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
List Of Aircraft Engines
This is an alphabetical list of aircraft engines by manufacturer. 0–9 2si *2si 215 *2si 230 * 2si 430 *2si 460 *2si 500 * 2si 540 * 2si 690 3W ''Source: RMV'' *3W 106iB2 *3W-110 *3W-112 *3W-170 *3W-210 *3W-220 A Abadal (Francisco Serramalera Abadal) *Abadal Y-12 350/400 hp ABC ''Source: Lumsden.'' * ABC 8 hp * ABC 30hp V-4 * ABC 45hp V-6 * ABC 60hp V-8 * ABC 85hp V-6 * ABC 100hp V-8 * ABC 115 hp * ABC 170hp V-12 * ABC 225hp V-16 * ABC Dragonfly *ABC Gadfly * ABC Gnat * ABC Hornet * ABC Mosquito * ABC Scorpion * ABC Wasp *ABC type 10 APU *ABC type 11 APU ABECO ''Source: RMV'' *ABECO GEM Aberg ''Source: RMV'' *Type Sklenar ABLE ''Source: RMV'', Able Experimental Aircraft Engine Co. (Able Experimental Aircraft Engine Co., Altimizer, Hoverhawk (US)) *ABLE 2275 *ABLE 2500 *ABLE VW x 2 Geared Drive Accurate Automation Corp *Accurate Automation AT-1500 *Accurate Automation AT-1700 Ace (Ace American Engr Corp, Horace Keane Aeroplane Co, North ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
IHI Corporation XF9
The IHI XF9 is a low-bypass afterburning turbofan engine developed by the Acquisition, Technology & Logistics Agency (ATLA) of Ministry of Defense of Japan (MoD) and IHI Corporation. Overview The XF9 is a product of an ATLA project ''Research on fighter engine system'' (2015–2019) which followed two preliminary projects, ''Research on main components of next generation engines'' (2010–2015) and ''Research on fighter engine elements'' (2013–2017). Started after development of the XF5 turbofan engine (1995–2008), these research projects are preliminary works for Japan's future fighter program or the successor to the Mitsubishi F-2 fighter. The basic concept is to produce a "slim and high-power" engine, thereby creating more capacity for accommodating fuel and weaponry inside the fuselage of stealth fighter to reduce radar cross section. The concept, dubbed High-power Slim Engine, also appears in an MoD report titled ''A vision for research and development of future fi ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
IHI Corporation F7
The IHI Corporation F7 is a small turbofan engine developed specifically for the Kawasaki P-1 maritime patrol aircraft by IHI Corporation. Development IHI started development work on the high bypass ratio turbofan engine in 1998, based on the low bypass ratio engine XF5-1. and the first prototype XF7-1 was tested from 2000 to 2002. The flight test XF7-10's testing started in 2002. XF7-10's PFRT (Preliminary Flight Rating Test) started in second quarter 2002, and was completed August 2007 before the XP-1 first flight. PFRT was based on the Military Specification MIL-E-5007D and the original standard about the FADEC system. Take off thrust is , bypass ratio is 8.2, and SFC is 0.34 kg/h/daN. Exhaust emission is under the ICAO's standard, NOx is 54%, CO is 33%, UHC is 0.5%, smoke is 74% when standard is 100%. Strong alloy materials were selected for high corrosion resistance in salt environments, and a sound absorbing panel is mounted. Noise level is 5~10 dB lower tha ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
IHI Corporation XF5
The Ishikawajima-Harima Heavy Industries (IHI) XF5 is a low bypass turbofan engine developed in Japan by Ishikawajima-Harima Heavy Industries for the Mitsubishi X-2 Shinshin (ATD-X). Applications * Mitsubishi X-2 Shinshin The Mitsubishi X-2 Shinshin (, formerly the ATD-X) is a Japanese experimental aircraft for testing advanced stealth fighter aircraft technologies. It is being developed by the Japanese Ministry of Defense Technical Research and Development Ins ... Specifications (XF5-1) See also References {{Japan military gas turbine aeroengines XF5 Low-bypass turbofan engines 2010s turbofan engines ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Axial Compressor
An axial compressor is a gas compressor that can continuously pressurize gases. It is a rotating, airfoil-based compressor in which the gas or working fluid principally flows parallel to the axis of rotation, or axially. This differs from other rotating compressors such as centrifugal compressor, axi-centrifugal compressors and mixed-flow compressors where the fluid flow will include a "radial component" through the compressor. The energy level of the fluid increases as it flows through the compressor due to the action of the rotor blades which exert a torque on the fluid. The stationary blades slow the fluid, converting the circumferential component of flow into pressure. Compressors are typically driven by an electric motor or a steam or a gas turbine. Axial flow compressors produce a continuous flow of compressed gas, and have the benefits of high efficiency and large mass flow rate, particularly in relation to their size and cross-section. They do, however, require sever ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
WikiProject Aircraft
A WikiProject, or Wikiproject, is a Wikimedia movement affinity group for contributors with shared goals. WikiProjects are prevalent within the largest wiki, Wikipedia, and exist to varying degrees within sister projects such as Wiktionary, Wikiquote, Wikidata, and Wikisource. They also exist in different languages, and translation of articles is a form of their collaboration. During the COVID-19 pandemic, CBS News noted the role of Wikipedia's WikiProject Medicine in maintaining the accuracy of articles related to the disease. Another WikiProject that has drawn attention is WikiProject Women Scientists, which was profiled by '' Smithsonian'' for its efforts to improve coverage of women scientists which the profile noted had "helped increase the number of female scientists on Wikipedia from around 1,600 to over 5,000". On Wikipedia Some Wikipedia WikiProjects are substantial enough to engage in cooperative activities with outside organizations relevant to the field at issue. Fo ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Single Crystal
In materials science, a single crystal (or single-crystal solid or monocrystalline solid) is a material in which the crystal lattice of the entire sample is continuous and unbroken to the edges of the sample, with no grain boundaries.RIWD. "Reade Advanced Materials – Single Crystals". ''www.reade.com''. Retrieved 2021-02-28. The absence of the defects associated with grain boundaries can give monocrystals unique properties, particularly mechanical, optical and electrical, which can also be anisotropic, depending on the type of crystallographic structure. These properties, in addition to making some gems precious, are industrially used in technological applications, especially in optics and electronics. Because entropic effects favor the presence of some imperfections in the microstructure of solids, such as impurities, inhomogeneous strain and crystallographic defects such as dislocations, perfect single crystals of meaningful size are exceedingly rare in nature. The necess ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Combustor
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, 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 pressure as the fuel/air mix burns. As it burns the fuel/air mix heats and rapidly expands. The burned mix is exhausted from the combustor through the nozzle guide vanes to the turbine. In the case of a ramjet or scramjet engines, the exhaust is directly fed out through the nozzle. A combustor must contain and maintain stable combustion despite very high air flow rates. To do so combustors are carefully designed to first mix and ignite the air and fuel, and then mix in more air to complete the combustion process. Early gas turbine engines used a single chamber known as a can-type combustor. Today three main configurations exist: can, annular, and ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
Thrust Vectoring
Thrust vectoring, also known as thrust vector control (TVC), is the ability of an aircraft, rocket, or other vehicle to manipulate the direction of the thrust from its engine(s) or motor(s) to control the attitude or angular velocity of the vehicle. In rocketry and ballistic missiles that fly outside the atmosphere, aerodynamic control surfaces are ineffective, so thrust vectoring is the primary means of attitude control. Exhaust vanes and gimbaled engines were used in the 1930s by Robert Goddard. For aircraft, the method was originally envisaged to provide upward vertical thrust as a means to give aircraft vertical (VTOL) or short (STOL) takeoff and landing ability. Subsequently, it was realized that using vectored thrust in combat situations enabled aircraft to perform various maneuvers not available to conventional-engined planes. To perform turns, aircraft that use no thrust vectoring must rely on aerodynamic control surfaces only, such as ailerons or elevator; aircraf ... [...More Info...] [...Related Items...] OR: [Wikipedia] [Google] [Baidu] |
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