V31 发动机辅助系统及其附件 标准查询与下载

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

SAE ARP5454A-2008 航空航天动力和推动力润滑系统中使用的精制润滑油过滤部件的过滤性能评估用多相方法

This SAE Aerospace Recommended Practice (ARP) describes the multi-pass method for evaluating the filtration performance of fine lube filter elements, commonly utilized in aerospace power and propulsion lubrication systems: gas turbine engines, auxiliary power units (APUs), helicopter transmissions, constant speed drives (CSDs), and integrated drive generators (IDGs).

Multi-Phase Method for Evaluating Filtration Performance of Fine Lube Filter Elements Utilized in Aerospace Power and Propulsion Lubrication Systems

SAE AS4191-2008 使用公式翻译程式语言的计算机程序中的燃气涡轮发动机的性能表现[代替:SAE ARP 4191C,SAE ARP 4191B,SAE ARP 4191A]

This SAE Aerospace Standard (AS) provides a method for gas turbine engine performance computer programs to bewritten using FORTRAN COMMON blocks. If a “function-call application program interface” (API) is to be used, thenARP4868 and ARP5571 are recommended as alternatives to that described in this document.When it is agreed between the program user and supplier that a particular program shall be supplied in FORTRAN, thisdocument shall be used in conjunction with AS681 for steady-state and transient programs.This document also describes how to take advantage of the FORTRAN CHARACTER storage to extend the informationinterface between the calling program and the engine subroutine.

Gas Turbine Engine Performance Presentation for Computer Programs Using FORTRAN [Superseded: SAE ARP 4191C, SAE ARP 4191B, SAE ARP 4191A]

GJB 6357-2008 直升机涡轴发动机减速器通用规范

本规范规定了直升机涡轴发动机减速器(以下简称减速器)的设计、性能、试验和验收的通用性要求。 本规范适用于直升机涡轴发动机减速器研制、生产和验收；也适用于涡桨发动机、桨扇发动机、涡扇发动机减速器和由两台发动机组成动力系统的并车减速器以及燃气涡轮起动机减速器。 对于已经批生产的减速器进行改进改型时，亦可参照本规范对其改动的部分进行设计和验证。

General specification for helicopter turboshaft engine reduction gearbox

HB 7827-2008 航空发动机飞行台通用技术要求

本标准规定了航空发动机飞行台设计、制造（改装）和验证的一般要求和详细要求。 本标准适用于涡喷、涡扇、涡桨发动机飞行台设计、制造（改装）和建成后的试验验证。涡轴发动机飞行台可参照使用。

General technical requirement for aeroengine flight test bed

SAE ARP4418A-2008 航空器发动机气源放气中发动机和APU产生污染物的取样和测量用实施规程

Aircraft propulsion engine and APU manufacturers shall demonstrate that air provided to the aircraft cabin is of acceptable quality. This ARP provides the basic information required to perform an engine bleed air quality certification test. This document provides the recommended levels and describes the measurement procedures required for the quantification of gaseous and particulate contaminants, which may be present in aircraft engine bleed air. Recommended techniques for engine sampling and sample transfer are given, together with specific analytical methodology, for each of the contaminants listed in Section 3. Recommendations are also made for an engine test format and for the allowance of ambient air quality on the measured engine contaminant concentration levels. The list and recommended limits of contaminants in Table 1 are considered appropriate for the certification and passenger safety requirements of both civil and military aircraft. If testing is performed on the aircraft, the operator should be aware that other sources of contamination may be present.

(R) Procedure for Sampling and Measurement of Engine and APU Generated Contaminants in Bleed Air Supplies from Aircraft Engines

ASTM F2689-08 无人飞机系统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 unmanned aircraft systems design requirements 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. Compliance with this specification is intended to demonstrate an adequate level of reliability in accordance with the UAS safety objectives.1.1 This practice covers minimum requirements for the design and manufacture of reciprocating spark ignition engines for unmanned aircraft systems. 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 Unmanned Aircraft Systems

GJB 6065-2007 航空涡轮发动机电点火系统通用规范

本规范规定了航空涡轮发动机电点火系统的通用要求。 本规范适用于航空涡轮发动机电点火系统（以下简称点火系统）。

General specification for electrical ignition system of aircraft turbine engine

HB 7810-2006 航空燃气涡轮发动机润滑系统滑油消耗量测量方法

本标准规定了航空燃气涡轮发动机滑油消耗量的测量方法。 本标准适用于新设计和改进改型的航空燃气涡轮发动机在台架和外场使用条件下滑油消耗量的测量。

Oil consumption measurements for oil system of aircraft gas turbine engine

HB 7800-2006 飞机发动机进气道及机体系统结冰探测器通用规范

本规范规定了飞机发动机进气道及机体系统结冰探测器（以下简称结冰探测器）的技术要求和质量保证规定。 本规范适用于结冰探测器的设计、研制、生产和检验。

General specification for detector ice of air intake duct aircraft engines and airframe systems

HB 7812-2006 燃气轮机机组箱装体通用技术要求

本标准规定了燃气轮机机组的箱装体结构、噪声控制、消防灭火和通风空调等通用技术要求。 本标准适用于发电和机械驱动用燃气轮机机组箱装体的技术要求。舰船用燃气轮机机组箱装体可参照使用。

General requirements of gas turbine assembly enclosure

HB 7811-2006 燃气轮机成套设备进排气系统通用技术要求

本标准规定了燃气轮机成套设备进、排气系统（以下简称进排气系统）中进气过滤装置、消声装置、余热利用设备、低排放设备等通用技术要求。 本标准适用于燃气轮机发电设备。燃气轮机试车台和以燃气轮机为动力的压气机试验台、注水泵站、天然气增压站等的进、排气系统可参照使用。

General requirements for inlet and exhaust systemof gas turbine Turnkey installation

HB 7813-2006 燃气轮机增压机组通用技术要求

本标准规定了燃气轮机增压机组（以下简称机组）的主要参数、结构形式、系统、测量、环境及保护等通用技术要求。 本标准适用于天然气管道输送用燃气轮机增压机组的设计、采购。其他燃气轮机增压机组可参照使用。

General requirements for gas turbine supercharging unit

SAE AIR5120-2006 发动机监测系统的可靠性和有效性

For Engine Monitoring Systems to meet their potential for improved safety and reduced operation and support costs, significant attention must be focused on their reliability and validity throughout the life cycle. This AIR will provide program managers, designers, developers and customers a concise reference of the activities, approaches and considerations for the development and verification of a highly reliable engine monitoring system. When applying the guidelines of this AIR it should be noted that engine monitoring systems physically or functionally integrated with the engine control system and/or performing functions that affect engine safety or are used to effect continued operation or return to service decisions shall be subject to the Type Investigation of the product in which theyll be incorporated and have to show compliance with the applicable airworthiness requirements as defined by the responsible Aviation Authority. This is not limited to but includes the application of software levels consistent with the criticality of the performed functions. For instance, low cycle fatigue (LCF) cycle counters for Engine Critical Parts would be included in the Type Investigation but most trend monitors and devices providing information for maintenance would not.

Engine Monitoring System Reliability and Validity

GJB 5785-2006 军用内燃发电机组通用规范

本规范规定了军用直流、工频（50Hz）、中频（400Hz）和双频（50Hz、400Hz）内燃发电机组的通用要求、质量保证规定和交货准备等要求。 本规范适用于0.5KW～315KW军用内燃发电机组（以下简称机组）的研制、生产、检验、验收等。

General specification for military generating sets with internalcombustion engines

GJB 5845-2006 液体推进剂钛合金贮箱通用规范

本规范规定了液体推进剂钛合金贮箱（以下简称贮箱）的通用要求。 本规范适用于航天器液体推进剂钛合金贮箱产品的设计、制造、试验和验收，其它类型推进剂贮箱可参照使用。

General specification for liquid propellant tank of titanic alloy

GJB 5848-2006 发射场卫星推进剂泄漏检测方法

本标准规定了发射场卫星推进剂泄漏检测环境、检测仪器、检测要求及检测程序等。 本标准适用于发射场卫星单组元推进剂（无水肼）和双组元推进剂（甲基肼、四氧化二氮）的泄漏检测。发动机试车台及推进剂生产、贮藏、运输可参照使用。运载火箭推进剂系统也可参照使用。

Detection methods of propellant leak for satellite on launching site

SAE AIR790C-2006 航空器燃料系统中冻结成冰的考虑

Ice formation in aircraft fuel systems results from the presence of dissolved and undissolved water in the fuel. Dissolvedwater or water in solution with hydrocarbon fuels constitutes a relatively small part of the total water potential in aparticular system with the quantity dissolved being primarily dependent on the fuel temperature and the water solubilitycharacteristics of the fuel. One condition of undissolved water is entrained water such as water particles suspended in thefuel as a result of mechanical agitation of free water or conversion of dissolved water through temperature reduction.Another condition of undissolved water is free water which may be introduced as a result of refueling or the settling ofentrained water which collects at the bottom of a fuel tank in easily detectable quantities separated by a continuousinterface from the fuel above. Water may also be introduced as a result of condensation from air entering a fuel tankthrough the vent system.Entrained water will settle out in time under static conditions and may or may not be drained, depending on the rate atwhich it is converted to free water. In general, it is not likely that all entrained water can ever be separated from fuel underfield conditions. The settling rate depends on a series of factors including temperature, quiescence and droplet size. Thedroplet size will vary depending upon the mechanics of formation. Usually the particles are so small as to be invisible tothe naked eye, but in extreme cases can cause a slight haziness in the fuel.Free water can be drained from a fuel tank if low point drain provisions are adequate. Water in solution cannot beremoved except by dehydration or by converting it, through temperature reduction, to entrained, then to free water.Water strictly in solution is not a serious problem in aviation fuel so long as it remains in solution. Entrained and free waterare the most dangerous because of the potential of freezing on the surfaces of the fuel system. Further, entrained waterwill freeze in cold fuel and tend to stay in solution longer since the specific gravity of ice is approximately the same as thatof hydrocarbon fuels.The elimination of undissolved water, to the extent practicable, in fuel storage, handling and delivery systems as well as inaircraft fuel systems can reduce or eliminate the potential for icing problems. Appropriate testing of fuel systems, subsystems and components under controlled icing conditions can establish confidence in the safe operation of the aircraftfuel system in such icing conditions. Considerations for these measures to control potential icing problems are addressedherein.Several things happen to moisture laden fuel as the temperature is lowered, and an understanding of this helps to arriveat proper fuel conditioning procedures and subsequent testing for icing conditions. As the temperature of fuel is lowered,concentration of water droplets in the fuel begins to decrease in the vicinity of 40 to 50 °F (4 to 10 °C). Therefore, to get areliable conditioning of fuel, samples should be taken and mixing of fuel and water should be accomplished beforelowering the temperature further. Ice crystals begin to form as the temperature nears the freeze point of water; however,due to impurities in the water, this normally takes place at slightly lower temperatures (27 to 31 °F) (-3 to -1 °C). As thetemperature is lowered further, the ice crystals begin to adhere to their surroundings in the form of ice.

(R) Considerations on Ice Formation in Aircraft Fuel Systems

ARINC 768-1-2006 综合监视系统

INTEGRATED SURVEILLANCE SYSTEM (ISS)

INTEGRATED SURVEILLANCE SYSTEM (ISS)

GJB 4597A-2006 航空发动机履历本编制要求

本标准规定了军用航空发动机履历本的结构、内容、格式及编制要求。 本标准适用于各类军用航空发动机履历本（以下简称为履历本）的编制和使用。

Requirement for preparation of logbook for aero-engine