V30 发动机总体 标准查询与下载

DLA MS27249 REV E VALID NOTICE 3-2006 可组合的接线端子板

MS27249E, dated 03 January 2000, remains inactive for new design; however, the document is valid for use.

TERMINAL BOARDS, SECTIONAL

SAE ARP876E-2006 燃气涡轮喷气机发出噪音预报

ARP876 is intended to provide specific recommended procedures for the prediction of gas turbine jet exhaust system noise sources. Procedures are issued as separate Sections, to allow for future updating as additional methods, consistent with state-of-the-art, become available.

Gas Turbine Jet Exhaust Noise Prediction

ASTM F2339-06 轻型运动飞行器用往复式火花点火式发动机的设计和制造的标准实施规程

1.1 This practice covers minimum requirements for the design and manufacture of reciprocating spark ignition engines for light sport aircraft, VFR use.This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety and health practices and determine the applicability of regulatory limitations prior to use.

Standard Practice for Design and Manufacture of Reciprocating Spark Ignition Engines for Light Sport Aircraft

SAE ARP5107B-2006 电子发动机控制系统用限时调度(TLD)分析的指南

This SAE Aerospace Recommended Practice (ARP) provides methodologies and approaches which have been used for conducting and documenting the analyses associated with the application of time limited dispatch (TLD) to the thrust control reliability of full authority digital electronic control (FADEC) systems. The TLD concept is one wherein a redundant system is allowed to operate for a predetermined length of time with faults present in the redundant elements of the system, before repairs are required. This document includes the background of the development of TLD, the structure of TLD that was developed and implemented on present generation commercial transports, and the analysis methods used to validate the application of TLD on present day FADEC equipped aircraft. Although this document is specific to TLD analyses (for FADEC systems) of the loss of thrust control, the techniques and processes discussed in this document are considered applicable to other FADEC system failure effects or other redundant systems, such as, thrust reverser, and propeller control systems, and overspeed protection systems.

Guidelines for Time-Limited-Dispatch (TLD) Analysis for Electronic Engine Control Systems

ASTM F2339-06(2009) 轻型运动飞行器用往复式火花点火式发动机的设计和制造的标准实施规程

This practice provides designers and manufacturers of engines for light sport aircraft design references and criteria to use in designing and manufacturing engines. Declaration of compliance is based on testing and documentation during the design and testing or flight testing of the engine type by the manufacturer or under the manufacturers'' guidance.1.1 This practice covers minimum requirements for the design and manufacture of reciprocating spark ignition engines for light sport aircraft, VFR use. 1.2 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety and health practices and determine the applicability of regulatory limitations prior to use.

Standard Practice for Design and Manufacture of Reciprocating Spark Ignition Engines for Light Sport Aircraft

HB 7783-2005 航空涡轮发动机点火系统通用规范

本规范规定了航空燃气涡轮发动机电点火系统的技术要求和质量保证规定。 本规范适用于航空燃气涡轮发动机电点火系统的研制。

Ignition system, aircraft turbine engine, general specification for

HB 7774.1-2005 基于UG航空发动机建模要求 第1部分：通用要求

本部分规定了应用Unigraphics 工程软件实施发动机三维建模及二维制图的通用要求。 本部分适用于航空发动机和航空发动机附件三维零组件设计，同时适用于航空发动机数字样机的建立。

Requirement for aeroengine modeling in Unigraphics--Part 1: General requirements

HB 7766-2005 燃气轮机成套设备安装通用技术要求

本标准规定了燃气轮机及其成套设备（以下简称成套设备）的安装要求。 本标准适用于发电用燃气轮机成套设备的安装。舰船用、机械驱动用的燃气轮机成套设备可参照执行。

Installation general requirements of gas Turbine turnkey installation

SAE ARP5571-2005 面向对象的程序设计的数字计算机的燃气涡轮发动机性能表示和术语

This document provides recommendations for several aspects of air-breathing gas turbine engine performance modeling using object-oriented programming systems. Nomenclature, application program interface, and user interface are addressed with the emphasis on nomenclature. The Numerical Propulsion System Simulation (NPSS) modeling environment is frequently used in this document as an archetype. Many of the recommendations for standards are derived from NPSS standards. NPSS was chosen because it is an available, production system. The practices recommended herein may be applied to other object oriented systems. While this document applies broadly to any gas turbine engine, the great majority of engine performance computer programs have historically been written for aircraft propulsion systems. Aircraft and propulsion terminology and examples appear throughout. The purpose of this document is to define an object-oriented paradigm for the simulation of gas turbine engine performance, recommend nomenclature for objects and variables within such a simulation, and recommend standards for user interaction with such a simulation.

Gas Turbine Engine Performance Presentation and Nomenclature for Digital Computers Using Object-Oriented Programming

SAE AIR4985-2005 工程监测系统效能的合格鉴定法

The purpose of this SAE Aerospace Information Report (AIR) is to present a quantitative approach for evaluating the performance and capabilities of an engine monitoring system (EMS). The value of such a methodology is in providing a systematic means to accomplish the following: 1. Determine the impact of an EMS on key engine supportability indices such as fault detection rate, fault isolation rate, mean time to diagnose, in-flight shutdowns (IFSD), mission aborts, and unscheduled engine removals (UERs). 2. Facilitate trade studies during the design process sin order to compare performance versus cost for various EMS design strategies, and 3. Define a common language for specifying EMS requirements and the design features of an EMS in order to reduce ambiguity and, therefore, enhance consistency between specification and implementation. The techniques used for this methodology borrow from those used for testability analysis and are modified to apply to the unique aircraft supportability definitions in item 1 above. While the discussion and examples in this document focus on aircraft engines and their components, the methods and terms in this AIR are applicable to other systems. For example starting systems can be considered to be within the scope of the document. It will be noted that many of the terms and measures used in the document reflect a military bias. It is anticipated that the methods described will either apply directly to commercial aviation measures or can be readily adapted.

A Methodology for Quantifying the Performance of an Engine Monitoring System

ASTM F2339-05 轻型运动飞行器用往复式火花点火式发动机的设计和制造的标准实施规程

1.1 This practice covers minimum requirements for the design and manufacture of reciprocating spark ignition engines for light sport aircraft, day VFR use.1.2 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety and health practices and determine the applicability of regulatory limitations prior to use.

Standard Practice for Design and Manufacture of Reciprocating Spark Ignition Engines for Light Sport Aircraft

NF L90-335-1:2004 空间工程.机械的.第5-1部分:航空器的液体和电推进器

Space engineering - Mechanical - Part 5-1 : liquid and elecric propulsion for spacecraft.

ASTM D6812-04 涡轮增压/增压火花点火式航空发动机的地面辛烷值测定的标准实施规程

1.1 This practice covers ground-based octane rating procedures for turbocharged/supercharged spark ignition aircraft engines. This practice has been developed to allow the widest range of applicability possible but may not be appropriate for all engine types. This practice is specifically directed to ground-based testing and actual in-flight octane ratings may produce significantly different results.1.2 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety and health practices and determine the applicability of regulatory limitations prior to use.

Standard Practice for Ground-Based Octane Rating Procedures for Turbocharged/Supercharged Spark Ignition Aircraft Engines

ASTM D6812-04a 涡轮增压/增压火花点火式航空发动机的地面辛烷值测定的标准实施规程

This practice is used as a basis for determining the minimum ground-based octane requirement of turbocharged/supercharged aircraft engines by use of PRFs and RFs. Results from standardized octane ratings will play an important role in defining the octane requirement of a given aircraft engine, which can be applied in an effort to determine a fleet requirement.1.1 This practice covers ground-based octane rating procedures for turbocharged/supercharged spark ignition aircraft engines. This practice has been developed to allow the widest range of applicability possible but may not be appropriate for all engine types. This practice is specifically directed to ground-based testing and actual in-flight octane ratings may produce significantly different results.1.2 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety and health practices and determine the applicability of regulatory limitations prior to use.

Standard Practice for Ground-Based Octane Rating Procedures for Turbocharged/Supercharged Spark Ignition Aircraft Engines

ANSI/ASTM D6812b:2004 涡轮增压/增压式火花点火式飞行器发动机的地面站辛烷值法实施规程

PRACTICE FOR GROUND-BASED OCTANE RATING PROCEDURES FOR TURBOCHARGED/SUPERCHARGED SPARK IGNITION AIRCRAFT ENGINES

ASTM D6812-04a(2010) 涡轮增压/增压火花点火式航空发动机的地面辛烷值测定的标准实施规程

This practice is used as a basis for determining the minimum ground-based octane requirement of turbocharged/supercharged aircraft engines by use of PRFs and RFs. Results from standardized octane ratings will play an important role in defining the octane requirement of a given aircraft engine, which can be applied in an effort to determine a fleet requirement.1.1 This practice covers ground-based octane rating procedures for turbocharged/supercharged spark ignition aircraft engines. This practice has been developed to allow the widest range of applicability possible but may not be appropriate for all engine types. This practice is specifically directed to ground-based testing and actual in-flight octane ratings may produce significantly different results. 1.2 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety and health practices and determine the applicability of regulatory limitations prior to use.

Standard Practice for Ground-Based Octane Rating Procedures for Turbocharged/Supercharged Spark Ignition Aircraft Engines

ANSI/ASTM D6424a:2004 测定自燃吸气火花点火式飞机发动机燃料辛烷值的操作规程

This practice covers ground based octane rating procedures for naturally aspirated spark ignition aircraft engines using primary reference fuels. This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety and health practices and determine the applicability of regulatory limitations prior to use.

PRACTICE FOR OCTANE RATING NATURALLY ASPIRATED SPARK IGNITION AIRCRAFT ENGINES

ASTM F2339-04 轻型运动飞机用往复式火花点火式发动机的设计和制造的标准实施规程

1.1 This practice covers minimum requirements for the design and manufacture of reciprocating spark ignition engines for light sport aircraft, day VFR use.1.2 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety and health practices and determine the applicability of regulatory limitations prior to use.

Standard Practice for Design and Manufacture of Reciprocating Spark Ignition Engines for Light Sport Aircraft

ISO/TR 17400:2003 航天系统.航天全套发射装置、集成站和其他设备.通用测试指南

This Technical Report is applicable to new projects and programs and to redesigned and upgraded launch pad and integration sites. This Technical Report establishes the testing phases, goals, and general aspects for launch space complexes and complexes for assembly and tests of a vehicle and spacecraft and the associated equipment that, after successful testing, will be ready for launch vehicle processing and launch. This Technical Report may be applicable to the creation of international launch pad and integration sites. At creation of new launching space complexes and complexes for assembly and tests of a vehicle and spacecraft (or at their modernization) within the framework of one country, the rules established by that country may be applied.

Space systems - Space launch complexes, integration sites and other facilities - General testing guidelines

ASTM D6812-03 涡轮增压火花点火式飞机发动机用地面站燃料辛烷值测定的标准实施规范

1.1 This practice covers ground-based octane rating procedures for turbocharged/supercharged spark ignition aircraft engines. This practice has been developed to allow the widest range of applicability possible but may not be appropriate for all engine types. This practice is specifically directed to ground-based testing and actual in-flight octane ratings may produce significantly different results.1.2 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety and health practices and determine the applicability of regulatory limitations prior to use.

Standard Practice for Ground-Based Octane Rating Procedures for Turbocharged/Supercharged Spark Ignition Aircraft Engines