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The Effect of Installation Power Losses on the Overall Performance of a Helicopter

S-12 Helicopter Powerplant 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 ensure…
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Performance of Low Pressure Ratio Ejectors for Engine Nacelle Cooling

S-12 Helicopter Powerplant 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 Helicopter Powerplant 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 Helicopter Powerplant 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 Helicopter Powerplant 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 Helicopter Powerplant 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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Helicopter Mission Definition

S-12 Helicopter Powerplant Committee
  • Aerospace Standard
  • ARP1352
  • Current
Published 1997-12-01 by SAE International in United States
The purpose of this recommended practice is to establish a standard format for the presentation of helicopter mission data, which will provide data required to establish airframe and/or engine component life.
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Helicopter Power Assurance

S-12 Helicopter Powerplant Committee
  • Aerospace Standard
  • AIR4083A
  • Current
Published 1997-06-01 by SAE International in United States
This SAE Aerospace Information Report (AIR) defines helicopter turboshaft engine power assurance theory and methods. Several inflight power assurance example procedures are presented. These procedures vary from a very simple method used on some normal category civil helicopters, to the more complex methods involving trend monitoring and rolling average techniques. The latter method can be used by small operators but is generally better suited to the larger operator with computerized maintenance record capability.
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Cockpit Information Required for Helicopter Turbine Engine Operation and Maintenance

S-12 Helicopter Powerplant Committee
  • Aerospace Standard
  • AIR1963A
  • Current
Published 1997-06-01 by SAE International in United States
This SAE Aerospace Information Report (AIR) identifies Propulsion Engineer’s recommendations for the instrumentation that is required for the safe operation and maintenance of turbine engines as installed in helicopters. It should be used as a guide for cockpit layout, as well as a reference for maintenance considerations throughout the propulsion area. Propulsion instruments should receive attention early in the design phase of the helicopter. Maintenance and diagnostics recorders are not considered within the scope of this document. (See ARP1587, “Aircraft Gas Turbine Engine Monitoring System Guide”.)
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Twin Engine Helicopter Power Requirements

S-12 Helicopter Powerplant Committee
  • Aerospace Standard
  • AIR1850A
  • Current
Published 1997-06-01 by SAE International in United States
This SAE Aerospace Information Report (AIR) defines the power spectrum during normal and emergency operations of a twin engine helicopter and thereby postulates suitable power plant rating structures. This document does not address the power requirements for single engine helicopters or those with more than two engines.
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