Refine Your Search

Date

Date

Topic

Topic

Military aircraft Exhaust systems Aerospace S-12 Powered Lift Propulsion Committee Parts and Components Corrosion Logistics Human Factors and Ergonomics

Search Results

Viewing 1 to 20 of 20
1
Sort by title
Standard

Twin Engine Helicopter Power Requirements
1997-06-01
CURRENT
AIR1850A
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.
Standard

Turbine Drive Shaft Connection
2023-01-20
CURRENT
ARP721
This ARP applies to turbine engines that are to be used in helicopters. It provides the engine designer guide lines in achieving a satisfactory turbine engine drive shaft connection.
Standard

Performance of Low Pressure Ratio Ejectors for Engine Nacelle Cooling
1999-03-01
CURRENT
AIR1191A
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.
Standard

PERFORMANCE OF LOW PRESSURE RATIO EJECTORS FOR ENGINE NACELLE COOLING
1989-05-01
HISTORICAL
AIR1191
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.
Standard

Helicopter Powerplant Corrosion Protection
2023-02-06
CURRENT
AIR4495
This SAE Aerospace Information Report (AIR) describes the different aspects of corrosion on helicopter powerplants, on the components that are affected, and the subsequent consequences on the helicopter, engine durability, performance, and dependability. Guidelines that minimize corrosion during the design stage and during service operation are also discussed.
Standard

Helicopter Mission Definition
2022-02-23
WIP
ARP1352A
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.
Standard

Helicopter Mission Definition
1997-12-01
CURRENT
ARP1352
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.
Standard

HELICOPTER ENGINE FOREIGN OBJECT DAMAGE
1989-11-30
HISTORICAL
AIR4096
The purpose of this SAE Aerospace Information Report is to disseminate qualitative information regarding foreign object damage (FOD) to gas turbine engines used to power helicopters and to discuss methods of preventing FOD. Although turbine-powered, fixed-wing aircraft are also subject to FOD, the unique ability of the helicopter to hover above, takeoff from, and land on unprepared areas creates a special need for a separate treatment of this subject as applied to rotary-winged aircraft.
Standard

ENGINE EXHAUST SYSTEM DESIGN CONSIDERATIONS FOR ROTORCRAFT
2021-03-11
CURRENT
ARP4056
Turbine engines installed in rotorcraft have an exhaust system that is designed and produced by the aircraft manufacturer. The primary function of the exhaust system is to direct hot exhaust gases away from the airframe. The exhaust system may consist of a tailpipe, which is attached to the engine, and an exhaust fairing, which is part of the rotorcraft. The engine manufacturer specifies a baseline "referee" tailpipe design, and guaranteed engine performance is based upon the use of the referee tailpipe and tailpipe exit diameter. The configuration used on the rotocraft may differ from the referee tailpipe, but it is intended to minimize additional losses attributed to the installation. This Aerospace Recommended Practice (ARP) describes the physical, functional, and performance interfaces to be considered in the design of the aircraft exhaust system.
Standard

Air Bleed Objective for Helicopter Turbine Engines
1997-05-01
HISTORICAL
AIR984C
This SAE Aerospace Information Report (AIR) defines the helicopter bleed air requirements which may be obtained through compressor extraction and is intended as a guide to engine designers.
1
X