V30 发动机总体 标准查询与下载

GJB 6538-2008 航空涡轮喷气和涡轮风扇发动机翻修通用要求

本标准规定了航空涡轮喷气和涡轮购房发动机翻修的能用要求。 本标准适用于航空涡轮喷气和涡轮购房发动机翻修，是制定航空涡轮喷气和涡轮风扇发动机（以下简称发动机）型号翻修技术规范（以下简称技术规范）的基本依据。

General requirements for aircraft turbojet and aircraft turbofan engines overhaul

QJ 3310-2008 过氧化氢/煤油发动机地面试验方法

Hydrogen peroxide/kerosene engine ground test method

BS ISO 12257:2008 航空航天系列.内部六叶形轮驱动.米制系列

Aerospace - Internal six-lobe drives - Metric series

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

SAE AIR4782A-2008 消防龙头阀和耦合器的历史背景

This SAE Aerospace Information Report (AIR) presents historical information and background data related to hydrant valves and couplers used in worldwide ground refueling of commercial aircraft (hereafter generically referred to as hydrant devices). Military hydrant devices are not included since their mission requirements demand approaches that may differ.1.1 PurposeThe purpose of this document is to provide definitions, background and educational information for use by design engineers, users of the systems and other interested parties who are involved with hydrant devices and associated equipment.1.2 Field of ApplicationSoon after World War II, the military techniques for underwing refueling of turbine-engined aircraft were adopted for use on commercial aircraft. Advantages include significantly improved safety, convenience and rapidity of refueling.Refueling systems for commercial aircraft evolved to comprise five basic elements, as follows:a. Hydrant systems (or supply systems)b. Hydrant couplers (hydrant system to servicer systems)c. Servicer system (hydrant to aircraft)d. Aircraft couplings (service systems to aircraft fuel systems)e. Aircraft fuel systems Element (d), the aircraft couplings, are now true worldwide standards, having been adopted for military and commercialaircraft of all countries, and controlled by international standard documents.This document applies to the hydrant valve portions element (a), the entire element (b) and applicable portions of element (c). Some references to other elements are included, where pertinent.

Hydrant Valve and Coupler Historical Background

SAE AIR1903-2008 航空器无自动力系统

An airplane fuel tank inerting system provides an inert atmosphere in a fuel tank to minimize explosive ignition of fuel vapor.This AIR deals with the three methods of fuel tank inerting systems currently used in operational aircraft: (1) on-board inert gas generation systems (OBIGGS), (2) liquid/gaseous nitrogen systems and (3) Halon systems. The OBIGGS andnitrogen systems generally are designed to provide full-time fuel tank fire protection; the Halon systems generally are designed to provide only on-demand or combat-specific protection.This AIR does not treat the subject of Explosion Suppression Foam (ESF) that has been used for fuel tank explosion protection on a number of military aircraft. ESF is a totally passive, full-time protection system with multiple andsimultaneous hit capability up to 23 mm. The primary disadvantages of foam are weight, reduction of usable fuel, and theadded maintenance complexity when the foam must be removed for tank maintenance or inspection. AIR4170A is anexcellent reference for the use of ESF for fuel tank explosion protection [1].

Aircraft Inerting Systems

SAE AS681J-2008 计算机程序用燃气涡轮发动机表示法

This SAE Aerospace Standard (AS) provides the method for presentation of gas turbine engine steady-state and transientperformance calculated using computer programs. It also provides for the presentation of parametric gas turbine dataincluding performance, weight and dimensions computed by computer programs.This standard is intended to facilitate calculations by the program user without unduly restricting the method of calculationused by the program supplier. This standard is applicable to, but not limited to the following program types: datareduction, steady-state, transient, preliminary design, study, specification, status & parametric programs.

Gas Turbine Engine Presentation for Computer Programs

SAE AIR5871-2008 燃气涡轮发动机用预兆

1.1 PurposeThis document applies to prognostics of gas turbine engines and its related auxiliary and subsystems. Its purpose is to define the meaning of prognostics with regard to gas turbine engines and related subsystems, explain its potential and limitations, and to provide guidelines for potential approaches for use in existing condition monitoring environments. It also includes some examples.1.2 Field of ApplicationThis document seeks to meet the increasing interest in gas turbine engine prognostics. Specifically, the document tries to provide a timely guideline for applying prognostic technologies to enhance the capability of current monitoring and diagnostic systems. Some examples are provided that are intended to illustrate different approaches and methodologies.

Prognostics for Gas Turbine Engines

BS EN 4300:2008 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

GJB 1018A-2008 空空导弹固体火箭发动机通用规范

本规范规定了空空导弹固体火箭发动机的通用要求。 本规范适用于空空导弹固体火箭发动机(以下简称发动机)的研制、生产、检验、验收等。

General specification of solid propellant rocket motors for air-to-air guided missiles

GJB 6345-2008 军用直升机涡轮轴发动机设计定型试飞要求

本标准规定了直升机涡轮轴发动机设计定型飞行试验一般要求和各试验项目的试验条件、试验内容与方法、测量参数等的详细要求。 本标准适用于涡轮轴发动机设计定型试飞。

The flight test reguirements of design qualification for turboshaft engine of military helicopter

HB 7834-2008 航空发动机产品结构编码

本标准规定了航空发动机产品结构的编码原则和方法，并给出了相应的代码。 本标准适用于航空涡轮发动机的产品结构编码。

Coding for product structure of aeroengine

GJB 6260-2008 飞机发动机催化点火燃油控制器定时器规范

本规范规定了飞机发动机催化点火燃油控制器定时器（以下简称定时器）的要求、质量保证规定、交货准各。 本规范适用于涡扇飞机发动机燃油加力控制系统中定时控制部分。

Specification for timer of engine catalyzing ignition fuel adjuster

GJB 6196-2008 航空涡轮发动机点火系统加速试验方法

本标准规定了航空涡轮发动机电点火系统（由点火装置、点火电缆和产生电火花的电嘴组成，以下简称点火系统）加速试验的内容和方法。 本标准适用于航空涡轮发动机、燃气涡轮起动机及辅助动力装置的点火系统研制阶段对寿命的考核和对设计缺陷的确定。

Acceleration test means for ignition system of aircraft turbine engine

SAE ARP5757-2008 发动机元部件试验导则

This SAE Aerospace Recommended Practice (ARP) provides guidance for substantiating the airworthiness of aircraft engine components. Generally these components are associated with the engine control system, the system or systems that allow the engine to provide thrust or power as demanded by the pilot of the aircraft while also ensuring the engine operates within acceptable operating limits. But these components may also include hardware and systems associated with engine lubrication, engine or aircraft hydraulic or electrical systems, aircraft environmental control systems, thrust reverser control, or similar aircraft or engine propulsion system functions. This paper develops the concept of using a 26 item matrix of environmental conditions for evaluating aircraft engine component airworthiness. This approach is compatible with current practices used in the industry and has been accepted by engine certification authorities as part of engine certification programs. The purpose of this document is to provide guidance on demonstrating compliance with aircraft engine certification authority requirements for engine components. Many complete engine tests are done as part of the overall engine substantiation and certification process. But often during the engine testing process it is not practical to exercise all of the components of the engine to the extreme environmental limits each will encounter during operation in service. A simple example is during on the ground engine demonstrations the various components may not be exposed to the range of ambient temperature that will exist in the aircraft application. Additional tests or analysis may be required to demonstrate that the component will operate successfully throughout the range of ambient temperature conditions. There are a number other environmental conditions and combinations of conditions that can best be evaluated at the engine component or subsystem level. This ARP is written to address the engine components associated with a new engine program certification. But the guidance may also be used for validating design changes to previously certified engines. However, when using this ARP for substantiating design changes, all test parameter levels, times, and pass/fail criteria should be reviewed to make sure they are adequate for the already certified engine application.

Guidelines for Engine Component Tests

SAE AIR4061B-2008 带舱内航空器系统的发动机监测功能的集成用指南

SAE Aerospace Information Report (AIR) 4061 provides best practice guidelines for the integration of Engine Health Management (EHM) system functions within aircraft systems to include both its main engine(s) and any Auxiliary Power Unit(s) (APU). This document provides an overview of some of the functions EHM typically integrates, offers some system variations encountered with different aircraft, and suggests general considerations involved with integration. It presents a sample EHM parameter coverage matrix to show the types of parameters with which a typical EHM system might interface, offers insight into signal and data processing and retrieval, and offers a view of typical EHM parameter requirements by function. Where practical, this document delineates between military and commercial practices.

(R) Guidelines for Integrating Typical Engine Health Management Functions Within Aircraft Systems

SAE AIR1839C-2008 航空器涡轮发动机振动监测系统的指南

This Aerospace Information Report (AIR) is a general overview of typical airborne engine vibration monitoring (EVM) systems applicable to fixed or rotary wing aircraft applications, with an emphasis on system design considerations. It describes EVM systems currently in use and future trends in EVM development. The broader scope of Health and Usage Monitoring Systems, (HUMS ) is covered in SAE documents AS5391, AS5392, AS5393, AS5394, AS5395, AIR4174. The purpose of this AIR is to provide information and guidance for the selection, installation, and use of EVM systems and their elements. This AIR is not intended as a legal document but only as a technical guide.

(R) A Guide to Aircraft Turbine Engine Vibration Monitoring Systems

KS W 4020-2007 航空器推进系统设备通则

이 규격은 항공기의 추진 장비 계통(엔진 장비)의 기체 부분의 성능, 설계 및 시험에 대하

Installation of aircraft propulsion system, general specification for

QJ 3292-2007 固体火箭发动机燃烧室壳体焊缝X射线实时成像检测方法

X-ray Real-time Imaging Detection Method of Solid Rocket Motor Combustion Chamber Shell Weld

KS W 3223-2007 航空器.发动机空气起动连接装置

이 규격은 항공기 엔진 시동을 위한 공기원과의 접속부 치수를 규정한다. 이 치수는 커넥터

Aircraft-Connections for starting engines by air