V31 发动机辅助系统及其附件 标准查询与下载

HB 8584-2020 飞艇涵道转向系统通用要求

General requirement of airship turnable ducted propellers system

SAE AS194B-2014 命名.发动机冷却风扇

This Aerospace Standard (AS) covers the requirements for polytetrafluoroethylene (PTFE) hose assemblies for use in aerospace hydraulic fuel, and lubricating oil systems at temperatures between -67 degrees F and 450 degrees F for Class I assemblies, -67 degrees F and 275 degrees F for Class II assemblies, and at nominal pressures up to 1500 psi. The hose assemblies are also suitable for use within the same temperature and pressure limitations in aerospace pneumatic systems where some gaseous diffusion through the wall of the PTFE liner can be tolerated. The use of these hose assemblies in pneumatic storage systems is not recommended. In addition, installatio

Nomenclature - Engine Cooling Fan

SAE ARP719B-2013 燃气机

This document has been declared ""Stabilized"" and will no longer be subjected to periodic reviews for currency. Users are responsible for verifying references and continued suitability or technical requirements. New technology may exist. It is intended that this SAE Aerospace Recommended Practice (ARP) will set down guidelines for the development and test of gas motors to provide a practical and reliable hot gas rotary actuation mechanism. Specific operational and test requirements shall be specified in a detail specification. The areas to be discussed are: Requirements (performance, environment, life, and reliability), design and fabrication, and test con

Gas Motor

SAE AIR1419B-2013 气体涡轮发动机的进口总压力变形考虑因素

This document addresses may of the significant issues associated with effects of inlet total-pressure distortion on turbine-engine performance and stability. It provides a review of the development of techniques used to assess engine stability margins in the presence of inlet total-pressure distortion. Specific performance and stability issues that are covered by this document include total-pressure recovery and turbulence effects and steady and dynamic inlet total-pressure distortion.

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

SAE ARP876F-2013 燃气涡轮喷气发动机排气噪声预测

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

SAE ARP4868B-2013 用于燃气涡轮发动机性能程序的基于函数的应用程序接口(API)

The SAE Aerospace Standard document AS681 is the parent document of this SAE Aerospace Recommended Practice (ARP). AS681 applies to Engine programs written to conform to this document. This ARP specifies a set of functions and their expected behaviors that constitute a function based Application Program Interface (API) for gas turbine engine customer programs. The functions specified in this API are delivered by the Supplier as part of the Engine model. This document defines generic language independent functions and specific appendices for implementations in C and Fortran. The function based API specified in this ARP represents an alternative to the Fortra

Function-Based API for Gas Turbine Engine Performance Programs

SAE AIR1813B-2013 燃气涡轮发动机试验间噪声抑制用柯恩达效应/折射概念

This document has been declared ""Stabilized"" and will no longer be subjected to periodic reviews for currency. Users are responsible for verifying references and continued suitability or technical requirements. New technology may exist. Document provides information on how military/commercial/gas turbine engine test cell/system users may benefit from this unique Coanda//refraction concept. The information contains several factors which are considered essential for understanding the practical technical aspects of the concept. These are: a. operation need; b. concept definition; c. developmental program; and d. program results. To present an advanced techno

The Coanda/Refraction Concept for Gas Turbine Engine Test Cell Noise Suppression

SAE ARP4176-2013 实现发动机健全管理系统的成本和收益测定

This ARP provides an insight into how to approach a cost benefit analysis (CBA) to determine the return on investment (ROI) that would result from implementing a propulsion Prognostics and Health Management (PHM) system on an air vehicle. It describes the complexity of features that can be considered in the analysis, the different tools and approaches for conducting a CBA and differentiates between military and commercial applications. This document is intended to help those who might not necessarily have a deep technical understanding or familiarity with PHM systems but want to either quantify or understand the economic benefits (i.e., the value propositio

Determination of Costs and Benefits from Implementing an Engine Health Management System

SAE AIR5691-2013 燃料质量指示系统安装和设计导则

This document is applicable to commercial and military aircraft fuel quantity indication systems. It is intended to give guidance for system design and installation. It describes key areas to be considered in the design of a modern fuel system, and builds upon experiences gained in the industry in the last 10 years.

Guidance for the Design and Installation of Fuel Quantity Indicating Systems

SAE AS44B-2013 起动装置,安装垫片和驱动器,I, II, III, IV型

This document has been declared ""Stabilized"" and will no longer be subjected to periodic reviews for currency. Users are responsible for verifying references and continued suitability or technical requirements. New technology may exist. To establish essential minimum safe performance standards for Automatic Pilots primarily for use with turbine powered subsonic transport aircraft, the operation of which may subject the instrument to the environmental conditions specified in Section 3.3. This Aerospace Standard covers Automatic Pilots intended for use on aircraft to automatically operate the primary and trim aerodynamic controls to maintain stable flight a

Starters, Mounting Pads and Drives, Types I, II, III, IV

SAE AS100001D-2013 垫圈.X或XV型发动机辅机驱动

This document has been declared ""Stabilized"" and will no longer be subjected to periodic reviews for currency. Users are responsible for verifying references and continued suitability or technical requirements. New technology may exist.

Gasket - Type X or XV Engine Accessory Drive

ASME PTC 55-2013 燃气轮机飞机发动机.性能试验规范

This Code is only applicable to measuring performance when the engine is installed in a test facility. This Code is not applicable to measuring performance when the engine is installed in an aircraft, and it does not address engine-specific limits and margins. The Code does not cover ground-based mechanical or electrical power-generating gas turbines, which is the subject of PTC 22. This Code is not sufficient for certification or qualification of engines under development, nor is it intended for determination of research data. While this code does not cover the requirements for transient testing, it is recognized that transient testing may be required to meet some limited contractual requirements. Information on transient testing is provided herein to support a comprehensive test program.

Gas Turbine Aircraft Engines

MH/T 6089-2012 航空燃气涡轮发动机寿命使用监控和部件管理指南

Guidelines for Lifetime Monitoring and Components Management of Aviation Gas Turbine Engines

SAE AS3225C-2012 机盖.圆形,10.000螺栓圆周, AMS 4490 (UNS M11910)发动机附件传动装置

Cover - Engine Accessory Drive, Round, 10.000 Bolt Circle, AMS 4490 (UNS M11910)

SAE AIR4065A-2012 推进器/八叶螺旋桨飞行推力测定

This document has been declared "Stabilized" and will no longer be subjected to periodic reviews for currency. Users are responsible for verifying references and continued suitability or technical requirements. New technology may exist. AIR 4065, "Propeller/Propfan In-Flight Thrust Determination" addresses steady state propeller thrust as applied to aircraft which are usually powered by gas turbine engines. It includes theory, examples, and methods which have been used. Specifically two methods are discussed, the "J" or traditional J,Cp,Ct,ν method including the SBAC variation and a new method we call the "Theta" method which is dependent on knowing blade angle, power/torque and flight Mach number. Implementation guidelines are offered as well as overall approaches to flight testing. Appendices include expansions on theory and testing as well as examples.

Propeller/Propfan In-Flight Thrust Determination

SAE ARP6196-2012 燃气轮机发动机试验设备审核流程

This SAE Aerospace Recommended Practice provides recommendation for: the audit process in general; a list of specific areas of attention to be audited; maintaining the test facility in such a manner that it meets audit requirements.

Gas Turbine Engine Test Facility Audit Process

SAE AIR4068B-2012 燃气轮机发射探测器因素

This document has been declared "Stabilized" and will no longer be subjected to periodic reviews for currency. Users are responsible for verifying references and continued suitability of technical requirements. Newer technology may exist. This report describes the concept and data analysis of the probe factor (pf) scheme. Conclusions are drawn and recommendations made for action to further the requirements for improved methods and procedures in emissions sampling technology.

Gas Turbine Emission Probe Factors

SAE AMS3060B-2012 飞机发动机元件用防锈化合物

This specification covers a rust-inhibiting compound in the form of a liquid concentrate or a water soluble power. This product has been used typically in the preservation of steel engine components during overhaul, inspection, and re-assembly cycles of gas turbine engines, but usage is not limited to such applications.

Compound, Rust Inhibiting, Aircraft Engine Components

SAE AIR5687-2011 进气道/发动机兼容性.从模型到全尺寸开发

This document reviews the state of the art for data scaling issues associated with air induction system development for turbine-engine-powered aircraft. In particular, the document addresses issues with obtaining high quality aerodynamic data when testing inlets. These data are used in performance and inlet-engine compatibility analyses. Examples of such data are: inlet recovery, inlet turbulence, and steady-state and dynamic total-pressure inlet distortion indices. Achieving full-scale inlet/engine compatibility requires a deep understanding of three areas: 1) geometric scaling fidelity (referred to here as just "scaling"), 2) impact of Reynolds number, and 3) ground and flight-test techniques (including relevant environment simulation, data acquisition, and data reduction practices). The Model-to-Full Scale Subcommittee of the S- 16 Turbine Engine Inlet Flow Distortion Committee has examined archives and has obtained recollections of experts regarding air induction system development experience to produce this document. The primary objective of this document is to provide a consolidated record of what is known regarding the effectiveness of wind-tunnel scale-model testing in the prediction of full-scale flight characteristics such as inlet recovery, inlet turbulence, and steady-state and dynamic total-pressure inlet distortion. Discussion is offered regarding these findings in light of our current knowledge and understanding. Based on this discussion material, the SAE S-16 Committee has been able to achieve consensus on lessons learned and to provide recommendations.

Inlet / Engine Compatibility - From Model to Full Scale Development

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