V31 发动机辅助系统及其附件 标准查询与下载

SAE AIR5060A-2011 针对电磁环境效应的发动机电子控制设计指南

The purpose of this document is to provide reference material for establishing compatibility of electronic gas turbine engine control systems and associated components with the electromagnetic environment and achieving compliance with associated airworthiness requirements.

Electronic Engine Control Design Guide for Electromagnetic Environmental Effects

SAE ARP86C-2011 发动机废气进入空气换热器式飞机加热器

These recommendations are written to cover the subject of engine exhaust gas to air type heat exchangers under the following classifications: CABIN HEATING: (All occupied regions and windshields heating). Wing and empennage heating. ENGINE AND ACCESSORY HEATING: (When heater is installed as part of the aircraft). These recommendations are not intended to cover the design of secondary exchangers which may be required when engine exhaust gas to air type heat exchangers are used in supplying ventilating air.

Heater, Airplane, Engine Exhaust Gas to Air Heat Exchanger Type

SAE AIR999A-2011 低温燃料供给动态动力系统

For several years there has been increasing demand for self-contained, light-weight electrical and hydraulic power systems for various missile and other aerospace vehicle applications. This Aerospace Information Report intends to discuss one particular category known as Cryogenically Fueled Dynamic Power Systems. In this report, "Cryogenically Fueled Dynamic Power Systems" include all open cycle, chemically fueled, dynamic engine power systems which utilize cryogenic fuels and oxidizers. For nearly all practical present day systems, this category is limited to cryogenic hydrogen or hydrogen-oxygen fueled cycles with potential in future, more advanced systems for replacement of oxygen by fluorine. Excluded from the category are static cryogenic systems (e.g., fuel cells) and chemical dynamic power systems which utilize earth storable propellants.

Cryogenically Fueled Dynamic Power Systems

HB 20060-2011 航空发动机弹性支承器设计要求

本标准规定了航空发动机弹性支承器（以下简称弹性支承器）的设计准则、设计流程、设计内容和设计方法、验证试验项目。 本标准适用于航空燃气涡轮发动机弹性支承器设计。航空派生型燃气轮机及其他类型燃气轮机弹性支承器设计也可参照使用。

Damper design requirements of aero engine

HB 20042-2011 航空发动机转子轴向力试验方法

本标准规定了航空燃气涡轮发动机转子轴向力试验的一般要求、试验程序、数据处理及其结果评定等内容。 本标准适用于航空燃气涡轮发动机、压气机部件、涡轮部件等转子使用测力环测试系统的轴向力试验。

Test methods of rotor thrust for aircraft engine

HB 20062-2011 燃油系统单向活门通用规范

本规范规定了航空用燃油介质单向活门的技术要求和质量保证规定等内容。本规范适用于航空用燃油介质单向活门(以下简称产品)。

Fuel system check valve general specification

HB 20041-2011 航空发动机轴类部件疲劳试验方法

本标准规定了航空燃气涡轮发动机轴类部件疲劳试验的一般要求、试验程序、试验数据分析与处理、试验结果评定和试验报告编写等内容。 本标准适用于航空燃气涡轮发动机主轴(包括涡轮轴、压气机轴、动力涡轮轴和螺旋桨轴)或轴类部件的疲劳试验。

Shaft assembly fatigue tests of aircraft engine

QJ 20035-2011 液氧煤油发动机试验紧急关机程序

本标准规定了液氧煤油发动机地面试验故障紧急关机系统、故障判断、应用软件、试验准备和试验的要求。 本标准适用于液氧煤油发动机（以下简称"发动机"）地面试验缓变参数故障紧急关机系统。其它液体火箭发动机地面试验可参照使用。

Program for emergency cut-off of LOX/Kerosene rocket engine test

HB 6101-2011 航空滑油过滤器通用规范

本规范规定了航空用滑油过滤器的技术要求和质量保证规定等内容。 本规范适用于航空用滑油过滤器（以下简称滑油滤）。

Lubricate system filter general specification

HB 20061-2011 航空涡轮螺桨和涡轮轴发动机附件传动系统设计要求

本标准规定了航空涡轮螺桨和涡轮轴发动机附件传动系统的设计依据、设计准则、设计内容、设计流程、设计方法和验证试验项目。 本标准适用于航空涡轮螺桨和涡轮轴发动机附件传动系统的设计。航空涡轮风扇与涡轮喷气发动机、航空燃气涡轮辅助动力装置(APU)和地面燃气轮机附件传动系统也可参照使用。

Aero turboprop and turboshaft engine accessory transmission system design requirements

SAE ARP1256D-2011 航空涡轮发动机连续采样气体排放测量程序

This Aerospace Recommended Practice (ARP) describes the continuous sampling and analysis of gaseous emissions from aircraft gas turbine engines. The measured gas species include carbon monoxide (CO), carbon dioxide (CO2), nitric oxide (NO), nitrogen dioxide (NO2), total hydrocarbons (CHα where"α" is the hydrogen to carbon ratio of the fuel) and water vapor (H2O). This ARP excludes engine operating procedures and test modes, and is not intended for in-flight testing, nor does it apply to engines operating in the afterburning mode. It is recognized that there will probably be major advances in the gas analysis measurement technology. It is not the intent of this ARP to exclude other analysis techniques, but to form the basis of the minimum amount of conventional instruments (those in common industry usage over the last fifteen years) required for the analysis of aircraft engine exhaust. It is the responsibility of the analyst to demonstrate the alternative measurement technology has comparable (or better) performance, than the techniques described in this ARP. The measurement of other exhaust gas species is beyond the scope of this ARP. It should be noted the measurement of oxygen (O2) is generally accepted as essential for assessing data quality, but is not covered by this ARP. Sulfur dioxide (SO2) is normally not measured using conventional systems but is calculated from fuel sulfur content. Again this is not covered by this ARP.

Procedure for the Continuous Sampling and Measurement of Gaseous Emissions from Aircraft Turbine Engines

HB 20044-2011 航空燃气涡轮发动机转子动力特性试验要求

本标准规定了航空燃气涡轮发动机转子动力特性试验的一般要求、试验项目和试验程序、试验数据录取和处理、试验结果评定、试验报告编写。 本标准适用于航空燃气涡轮发动机转子在旋转试验器上的临界转速、振型、稳态不平衡响应(包括对不平衡的敏感度）、弹性支承-挤压油膜阻尼器减振特性试验。

Dynamic charateristic testing of aircraft gas turbine engine rotor

HB 20043-2011 航空燃气涡轮发动机转子高速动平衡试验方法

本标准规定了航空燃气涡轮发动机转子高速动平衡试验的一般要求、试验程序、试验数据录取与处理、试验结果评定、试验报告编写。 本标准适用于航空燃气涡轮发动机转子在旋转试验器上的高速动平衡试验。

High speed dynamic balance testing of aircraft gas turbine engine rotor

SAE AIR1419A-2011 气体涡轮发动机的进口总压力变形考虑因素

AIR1419 “Inlet Total Pressure Distortion Considerations for Gas Turbine Engines” documentsengineering information for use as reference material and for guidance. Inlet total-pressure distortionand other forms of flow distortion that can influence inlet/engine compatibility require examination toestablish their effect on engine stability and performance. This report centers on inlet-generated totalpressuredistortion measured at the Aerodynamic Interface Plane (AIP), not because this isnecessarily the sole concern, but because it has been given sufficient attention in the aircraft andengine communities to produce generally accepted engineering practices for dealing with it. Thereport does not address procedures for dealing with performance destabilizing influences other thanthose due to total-pressure distortion, or with the effects of any distortion on aeroelastic stability. Thepropulsion system designer must be careful to assure that, throughout the development process, otherforms of inlet flow distortion, which can have just as serious effects on system stability andperformance, have been effectively addressed.The report deals with spatial total-pressure distortion, as defined by an array of high-response totalpressureprobes. Time-variant total-pressure distortion, synthesized from statistical data, can provideuseful information. However, the consensus of SAE S-16 is that such techniques are not developedsufficiently to permit general guidelines to be formulated.

Inlet Total-Pressure-Distortion Considerations for Gas-Turbine Engines

SAE ARP1420B-2011 气体涡轮发动机进口气流畸变指南

The turbine-engine inlet flow distortion methodology addressed in this document applies only to theeffects of inlet total-pressure distortion. Practices employed to quantify these effects continue todevelop and, therefore, periodic updates are anticipated. The effects of other forms of distortion onflow stability and performance, and of any distortion on aeroelastic stability are not addressed.The guidelines can be used as necessary to create a development method to minimize the risk of inlet/engine compatibility problems. The degree to which guidelines for descriptor use, assessmenttechniques, and testing outlined in this document are applied to a specific program should beconsistent with the expected severity of the compatibility problem.

Gas Turbine Engine Inlet Flow Distortion Guidelines

ISO 10830:2011 航天系统.无损试验.固体火箭发动机石墨锭用自动超声波检测方式

Space systems - Non-destructive testing - Automatic ultrasonic inspection method of graphite ingot for solid rocket motors

SAE AIR1678B-2011 飞行中推力测定的不确定性

This document defines and illustrates the process for determination of uncertainty of turbofan and turbojet engine in-flight thrust and other measured in-flight performance parameters. The reasons for requiring this information, as specified in the E-33 Charter, are:- determination of high confidence aircraft drag; - problem rectification if performance is low; - interpolation of measured thrust and aircraft drag over a range of flight conditions by validation and development of high confidence analytical methods; - establishment of a baseline for future engine modifications. This document describes systematic and random measurement uncertainties and methods for propagating the uncertainties to the more complicated parameter, in-flight thrust. Methods for combining the uncertainties to obtain given confidence levels are also addressed. Although the primary focus of the document is in-flight thrust, the statistical methods described are applicable to any measurement process. The E-33 Committee has endeavored to gather industry-wide expertise in in-flight measurement and uncertainty analysis to collect and promulgate recommended practices in the subject disciplines. The Committee is organized into two subcommittees to address both the analytical and test methodology for determination of in-flight thrust and also the uncertainty of the determination. This document; Uncertainty of In-flight Thrust Determination, AIR1678, addresses the process for determining the uncertainty of in-flight thrust. A companion document, In-Flight Thrust Determination, AIR1703, addresses the basic methodology for determining in-flight thrust. The Committee, after reviewing recommended changes and clarification in definitions and application of statistical uncertainty items, have made small revisions to the original document published in 1985. These changes were incorporated into AIR1678 Rev. A. This Revision B has the same Scope as preceding versions. he nomenclature and methodology used herein are now consistent with evolving world and national standards promulgated primarily by ISO and ASME.

Uncertainty of In-Flight Thrust Determination

MH/T 3021-2011 燃气涡轮发动机燃油喷嘴测试

本标准规定了燃气涡轮发动机燃油喷嘴使用性能的基本测试条件、测试设备及测试的基本要求。 本标准适用于燃气祸轮发动机燃油喷嘴使用性能的测试。

Gas turbine engine fuel nozzle test procedures

SAE ARP5305-2010 封闭的涡轮风扇发动机/涡轮喷气飞机引擎测试单元的构设计与施工考虑

This SAE Aerospace Recommended Practice (ARP) is 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 constructing new or adding to existing engine test cell facilities. The purpose of this document is to provide general guidelines for the design and construction of concrete test cell structures that will resist the effects of normal engine operating loads, dynamic loads due to engine failure, over pressures and cell depression loads, acoustic and environmental loads and engine projectiles.

Structural Design and Construction Considerations for Enclosed Turbofan/Turbojet Engine Test Cells

SAE AIR5303-2010 英式试验机翼构架的次声现象

This SAE Aerospace Information Report (AIR) has been written for individuals associated with the ground level testing of large turbofan and turbojet engines, and particularly those who are interested in infrasound phenomena.

Infrasound Phenomenon in English Test Cells