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HELICOPTER ENGINE MOUNTING

S-12 Powered Lift Propulsion Committee
  • Aerospace Standard
  • AIR4172
  • Current
Published 2020-01-31 by SAE International in United States
This Aerospace Information Report (AIR) reviews the requirements to be satisfied by the engine mount systems and provides an outline of some suitable methods. Factors such as drive shaft alignment, engine expansion, mount crashworthiness, vibration isolation, and other effects on the installation are discussed.
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COOLING DATA FOR TURBINE ENGINES IN HELICOPTERS

S-12 Powered Lift Propulsion Committee
  • Aerospace Standard
  • ARP996A
  • Current
Published 2020-01-31 by SAE International in United States
A tested method of data presentation and use is described herein. The method shown is a useful guide, to be used with care and to be improved with use.
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CONCURRENT DESIGN OF ENGINES AND SPECIFICATIONS OF STARTING SYSTEMS FOR HELICOPTERS

S-12 Powered Lift Propulsion Committee
  • Aerospace Standard
  • AIR1296
  • Current
Published 2020-01-31 by SAE International in United States
It is recommended that all helicopter engine development programs include an evaluation of engine starting requirements. The evaluation should include starting requirement effects on helicopter weight, cost, and mission effectiveness. The evaluation should be appropriate to the engine stage of development.
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HELICOPTER TURBINE ENGINE WASH

S-12 Powered Lift Propulsion Committee
  • Aerospace Standard
  • AIR4416
  • Current
Published 2020-01-31 by SAE International in United States
Engines subject to dust, industrial pollution, saltwater contamination or other chemically laden atmosphere (including pesticides and herbicides) lose performance due to deposits of contaminants on surfaces in the aidgas flow path. Engine wash and engine rinse procedures are utilized to restore turbine engine performance. These procedures are generated by the engine manufacturer and are included in the Engine Maintenance/Service Manuals. For most turbine engines these procedures are similar in concept and practice; however, application details, choice of solvents and many other service features can vary from engine manufacturer to engine manufacturer and may even vary within the range of engine models produced by any manufacturer. The intent of this SAE Aerospace Information Report (AIR) is to outline the general nature, considerations, and background of engine wash and engine rinse and is directed towards the needs of the entry level engineer, service engineer, and those involved in the general maintenance of installed turbine engines.
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The Effect of Installation Power Losses on the Overall Performance of a Helicopter

S-12 Powered Lift Propulsion Committee
  • Aerospace Standard
  • AIR5642
  • Current
Published 2005-06-07 by SAE International in United States
The purpose of this SAE Aerospace Information Report (AIR) is to illustrate the effect of installation power losses on the performance of a helicopter. Installation power losses result from a variety of sources, some associated directly with the basic engine installation, and some coming from the installation of specific items of aircraft mission specific equipment. Close attention must be paid to the accurate measurement of these losses so that the correct aircraft performance is calculated. Installation power losses inevitably result in a reduction in the overall performance of the aircraft. In some cases, careful attention to detail will allow specific elements of the overall loss to be reduced with immediate benefit for the mission performance of the aircraft. When considering items of equipment that affect the engine, it is important to understand the effect these will have on overall aircraft performance to ensure that mission capability is not unduly compromised. Alternatively, a clear understanding of these effects at the aircraft design stage may have an influence on the initial choice of engine size to ensureā€¦
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Performance of Low Pressure Ratio Ejectors for Engine Nacelle Cooling

S-12 Powered Lift Propulsion Committee
  • Aerospace Standard
  • AIR1191A
  • Current
Published 1999-03-01 by SAE International in United States
A general method for the preliminary design of a single, straight-sided, low subsonic ejector is presented. The method is based on the information presented in References 1, 2, 3, and 4, and utilizes analytical and empirical data for the sizing of the ejector mixing duct diameter and flow length. The low subsonic restriction applies because compressibility effects were not included in the development of the basic design equations. The equations are restricted to applications where Mach numbers within the ejector primary or secondary flow paths are equal to or less than 0.3.
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Oil Systems for Helicopter Powerplants

S-12 Powered Lift Propulsion Committee
  • Aerospace Standard
  • AIR4281
  • Current
Published 1998-11-01 by SAE International in United States
Turbine engines installed in helicopters require a highly sophisticated oil system to fulfill two tasks: a Cooling/oil supply b Lubrication While lubrication is an engine internal procedure, cooling and oil supply require more or less design activity on the aircraft side of the engine/airframe interface for proper engine function, depending on the engine type. The necessity for engine cooling and oil supply provisions on the airframe can lead to interface problems because the helicopter manufacturer can influence engine related functions due to the design of corresponding oil system components. This SAE Aerospace Information Report (AIR) deals with integration of engine oil systems with the airframe and gives information for both helicopter and engine manufacturers for a better understanding of interface requirements.
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Defining and Measuring Factors Affecting Helicopter Turbine Engine Power Available

S-12 Powered Lift Propulsion Committee
  • Aerospace Standard
  • ARP1702A
  • Current
Published 1998-09-01 by SAE International in United States
This SAE Aerospace Recommended Practice (ARP) identifies and defines a method of measuring those factors affecting installed power available for helicopter power plants. These factors are installation losses, accessory power extraction, and operation effects. Accurate determination of these factors is vital in the calculation of helicopter performance as described in the flight manual. It is intended that the methods herein prescribe and define each factor as well as an approach to measuring said factor. Only standard installations of turboshaft engines in helicopters are considered. Special arrangements leading to high installation losses, such as the fitting of an infrared suppressor may require individual techniques for the determination and definition of engine installation losses.
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Helicopter FUEL Economy Evaluation

S-12 Powered Lift Propulsion Committee
  • Aerospace Standard
  • AS1516
  • Current
Published 1998-02-01 by SAE International in United States
The purpose of this standard is to provide a method of evaluating helicopter fuel economy which accounts for the significant technical variables in helicopter and powerplant design.
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Engine Erosion Protection

S-12 Powered Lift Propulsion Committee
  • Aerospace Standard
  • AIR947
  • Current
Published 1998-02-01 by SAE International in United States
This Aerospace Information Report deals with protection of helicopter aircraft engines against erosion. Applicability is restricted to aircraft having a disc loading of less than 15 pounds per square foot.
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