49.050 航空航天发动机和推进系统 标准查询与下载

SAE AIR4986A-2009 发动机静电气体通道监控

This document has been declared "CANCELLED" as of October 2009. By this action, this document will remain listed in the Numerical Section of the Aerospace Standards Index. Turbine engine malfunctions account for a substantial portion of the maintenance actions required to keep both fixed and rotary wing aircraft operational. Undetected incipient component failures can result in secondary engine damage and expensive unscheduled maintenance actions. Recent developments of electrostatic methods now provide the potential for the detection of foreign object ingestion and early detection of distress in gas path components. This SAE Aerospace Information Report (AIR) seeks to outline the history of the electrostatic technique and provides examples of state-of- the-art systems for both inlet and exhaust gas debris monitoring systems along with examples of most recent testing.

Engine Electrostatic Gas Path Monitoring

SAE ARP1827B-2009 航空器燃气涡轮发动机精细燃料过滤器元件性能测定方法

This SAE Aerospace Recommended Practices (ARP) delineates two complementary filter element performance ratings: (1) dirt capacity, and (2) filtration efficiency, and correpsonding test procedures. It is intended for the noncleanable (disposable), fine fuel filter elements used in aviation gas turbine engine systems. Variation in filter element testing methods and requirements make comparison of results difficult. In order to minimize these problems, this document describes standard filtration ratings and test procedures. Both manufacturer and customer will have a common means to specify, control, and evaluate filter elements

Measuring Aircraft Gas Turbine Engine Fine Fuel Filter Element Performance

DIN EN 4301:2009 航空航天系列.发动机的打印标号.工程要求.德文和英文版本EN 4301-2009

This standard describes the coding system for marks, the processes used to produce these marks, as well as the general marking requirements for the identification of aerospace engine items. This document is applicable to items whose engineering drawing or design folder refers to EN 4301 for all issues that are not in contradiction with specific indications appearing on the engineering drawing or in the design folder. This document is not applicable to items requiring an identification plate.

Aerospace series - Identification marking methods for engine items - Engineering requirements; German and English version EN 4301:2009

SAE AS1730C-2009 螺纹型刚性燃料管接头

The specification defines the requirements for a threaded rigid coupling assembly, which utilizes ferrule type machined tube end fittings, to join tubing and components in aircraft fuel, vent, and other systems. This coupling assembly is designed for use from -65 to 200 °F and at 125 psig operating pressure.

Coupling, Fuel, Rigid, Threaded Type

LST EN 4301-2009 航空航天系列发动机项目识别标记方法工程要求

Aerospace series - Identification marking methods for engine items - Engineering requirements

SAE AMS2647C-2009 飞行器与发动机部件维护中的荧光穿透探伤

This specification details requirements and procedures for the detection of defects in aircraft and engine components during maintenance and overhaul operations. This processes has been used typically by maintenance and overhaul facilities to inspect aircraft and engine components and associated accessories when fluorescent penetrant inspection is specified, but usage is not limited to such applications.

Fluorescent Penetrant Inspection Aircraft and Engine Component Maintenance

SAE AIR4869A-2009 封闭式涡轮风扇/涡轮喷射发动机测试腔的设计研究

This SAE Aerospace Information Report (AIR) has been written for individuals associated with the ground-level testing of large and small gas turbine engines and particularly for those who might be interested in upgrading their existing or acquiring new test cell facilities. There are several purposes served by this document: a. to provide guidelines for the design of state-of-the-art ground-level enclosed test facilities for turbofan and turbojet engine testing applications; b. to address the major test cell/engine aerodynamic and acoustic characteristics which can influence the operation of a gas turbine engine and its performance stability in a test cell; and c. to consider acoustic environmental impact and methods to control it.

Design Considerations for Enclosed Turbofan/Turbojet Engine Test Cells

BS EN 4301:2009 航空航天系列.引擎部件的识别标记法.工程要求

This standard describes the coding system for marks, the processes used to produce these marks, as well as the general marking requirements for the identification of aerospace engine items. This document is applicable to items whose engineering drawing or design folder refers to EN 4301 for all issues that are not in contradiction with specific indications appearing on the engineering drawing or in the design folder. This document is not applicable to items requiring an identification plate.

Aerospace series - Identification marking methods for engine items - Engineering requirements

DS/EN 4301:2009 航空航天系列发动机项目识别标记方法工程要求

This standard describes the coding system for marks, the processes used to produce these marks, as well as the general marking requirements for the identification of aerospace engine items.This document is applicable to items whose engineering drawing or design folder refers to EN 4301 for all issues that are not in contradiction with specific indications appearing on the engineering drawing or in the design folder.This document is not applicable to items requiring an identification plate.

Aerospace series - Identification marking methods for engine items - Engineering requirements

SAE ARP6028-2009 燃气涡轮发动机试验机翼构架的维护相关性用配置控制

The configuration of a test facility that exists at the time when a correlation is being carried out should be "base lined" as a condition of correlation approval acceptance, and, be maintained during the time period that the respective correlation approval lasts. This defines test facility configuration control. This is due to the fact that a change in configuration may have the potential to change the established correlation factors and measured engine performance. If such a change occurs then this should be judged by the respective OEM's or designated correlation approval authorities Subject Matter Expert (SME). In some cases, this may involve consultation with the engine project customer or airworthiness authorities. This paper can be considered applicable to all types and standards of test facilies in the aero, marine and industrial gas turbine engine businesses.

Configuration Control for Maintaining Correlation of Gas Turbine Engine Test Cells

EN 4301:2009 航空航天系列.发动机的打印标号.工程要求

This standard describes the coding system for marks; the processes used to produce these marks; as well as the general marking requirements for the identification of aerospace engine items.This document is applicable to items whose engineering drawing or design folder refers to EN 4301 for all issues that are not in contradiction with specific indications appearing on the engineering drawing or in the design folder.This document is not applicable to items requiring an identification plate.

Aerospace series - Identification marking methods for engine items - Engineering requirements

SAE AS1710D-2009 带套圈的螺纹型可变空腔柔性燃料耦合件

This SAE Aerospace Standard (AS) defines the requirements for a threaded flexible coupling assembly, which utilizes ferrules or machined tube end fittings to join tubing and components in aircraft fuel and fuel vent or other systems. This coupling assembly is designed for use from -65 to +200 °F and at 125 psig peak working pressure, and the coupling assembly may be used in other fluid systems when requirements are within the limits.

Coupling, Fuel, Flexible, Variable Cavity, Threaded Type With Ferrules

DIN EN 4300:2009 航空航天系列.发动机项目的识别标识.设计标准

This standard: describes the location and the layout of the marks of the item; describes the marking processes to be used according to the environment and the function of the items; determines the selection conditions of the marks; determines the compatibility conditions of the marking processes with the constitution, the production and the use of the items. This document applies to aerospace engine items and shall be used in conjunction with EN 4301.

Aerospace series - Identification marking of engine items - Design standard; German and English version EN 4300:2008

GOST R 53450-2009 航空发动机与发动机部件.工业用液压,油与燃料系统的清洁度.燃料系统清洁度等级

Aviation engines and engine components. Industrial cleanliness of hydraulic, oil and fuel systems. Fuel system cleanliness classes

GOST R 53541-2009 航空发动机及其组件.空气-燃气通道航空发动机及与之连接的空气-燃气系统分段上空气(燃气)状况的参数指数化

Aviation engines and their units. Indexation of parametres of air (gas) condition on sections of air-gas channel aviation engines and air-gas systems connected with them

GOST R 53542-2009 航空发动机及其部件.真空高合金钢硬钎焊.工艺过程的一般要求

Aviation engines and their components. Brazing of high-alloy steels in vacuum. General requirements for technological process

GOST R 53461-2009 航空发动机及其组件.旋转方向的编号与描述方法

Aviation engines and their assemblies. Methods of numbering and the description of a direction of rotation

GOST R 53374-2009 液体.火箭发动机.公共使用期间产品和质量检查的一般技术要求

Liquid - propellant rocket engines.General technical requirements for production and quality inspection during supply for use

LST EN 4300-2008 航空航天系列 发动机项目的识别标记 设计标准

Aerospace series - Identification marking of engine items - Design standard

SAE AIR5450-2008 高级管推进器空中推力测定

The emerging ultra high bypass ratio ADP engines, with nozzle pressure ratios significantly lower, and bypass ratios significantly higher, than those of the current turbofan engines, may present new in-flight thrust determination challenges that are not specifically covered in AIR1703. This document addresses candidate methods and the additional challenges to the thrust determination for these ADP engines.These novel challenges result in part from the fact that some large ADP engines exceed present altitude test facility capabilities. The traditional methods of nozzle coefficient extrapolation may not be most satisfactory because of the increased error due to the ADP higher ratio of gross to net thrust, and because of the increased sensitivity of in-flightthrust uncertainty at the lower fan nozzle pressure ratio. An additional challenge covered by this document is the higher ensitivity of ADP in-flight thrust uncertainty to the external flow field around the engine, and the changes in this flow fielddue to aircraft configuration and operations.Calibrations for in-flight thrust determination for these ADP engines may have to be based on other alternate methods.Recently, large size turbo powered simulators (TPS) of propulsion systems (including the nacelle) have been developed and thus provide a new capability for in-flight thrust determination. Furthermore Computational Fluid Dynamic (CFD) analysis may prove to be a viable supplement to ground (sea level) engine testing and sub-scale model coefficientextrapolations to cruise conditions. These recent developments are described within along with their associated error assessments.The candidate thrust methods build on the work presented in AIR1703. The document includes a comprehensive uncertainty assessment conducted per AIR1678 to identify the major thrust determination options. Fundamental to this uncertainty assessment are the influence coefficients relating in-flight thrust calculation uncertainty to the measuredparameters and derived coefficients. These influence coefficients were developed from three typical public domain, generic engine cycle models.For the major potential thrust determination options, the overall thrust and airflow calibration processes are defined in detail. Road maps are included showing model, engine and flight-tests, measurements and correlations, calibrationprocedures and analyses. The document addresses the pros and cons of each of the major thrust determination options, including a discussion of the key assumptions and expected uncertainties.1.1 Document RoadmapThe following schematic shows how to use this document. The type of thrust method used is dependent on several factors such as: the nature of the program itself and whether it’s a new aircraft and engine or a re-engine program; theperformance and guarantee requirements; the thrust accuracy required; the available budget; the power management parameter; etc.Sections 3 through 5 provide methodology and background information relevant to the challenges of integrating an ADP propulsion system into an aircraft. The key engineering activity to determine the validated in-flight thrust performance isfocused in Sections 6 through 9.

Advanced Ducted Propulsor In-Flight Thrust Determination