49.050 航空航天发动机和推进系统 标准查询与下载

SAE ARP1179D-2011 航空器燃气涡轮发动机排气烟度的测量

This SAE Aerospace Recommended Practice (ARP) standardizes test equipment and procedures for the measurement of smoke emission from aircraft gas turbine engines. The procedures included are for determining and reporting the amount of smoke emission. Tests have indicated that the practically achievable precision of the smoke number is within +3 when the system is properly used as outlined herein. This procedure is not intended for in-flight testing, nor does it apply to afterburning mode.

Aircraft Gas Turbine Engine Exhaust Smoke Measurement

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

SAE AIR4951-2011 测试单元推理测量

Thrust measurement systems come in many sizes and shapes, with varying degrees of complexity, accuracy and cost. For the purposes of this information report, the discussions of thrust measurement will be limited to axial thrust in single-axis test systems. These are several purposes served by this information report: a. To provide guidelines for the specification of thrust measurement systems; b. To address the major factors which can influence thrust measurement uncertainty; c. To consider the operational characteristics and the effects on system performance.

Test Cell Thrust Measurement

SAE AS5304-2011 对涡轮流量计的标准规格

This is a SAE Standard specification with minimum performance characteristics for Turbine Flowmeter (TFM) that pertains only to sizes from 1/2 to 2 inches. The utilization of TFM is for hydrocarbon liquid fuel volumetric flow measurements. This Standard specifically excludes smart electronics in accomplishing the defined performance objectives. Users of this Standard should specify other TFM characteristics required to satisfy their application and utilization in operational environment. A User should understand fit and function of the TFM and define end user specific fit and function requirements. The TFM should be calibrated by the manufacturer should be based upon end user requirements and presented as Roshko versus Strouhal at a reference temperature. The Supplier shall be prepared to show evidence to User that the device demonstrates compliance with all requirements identified in this Standard.

Standard Specification for Turbine Flowmeters

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

SAE AMS2647D-2011 荧光渗透剂检查法进行航空器和发动机组件维修

This specification details requirements and procedures for the detection of defects in aircraft and engine components during maintenance and overhaul operations.

Fluorescent Penetrant Inspection Aircraft and Engine Component Maintenance

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

ASTM F2840-11 设计和制造轻型运动飞机用电力推进装置的标准操作规程

This specification provides designers and manufacturers of electric propulsion for light sport aircraft design references and criteria to use in designing and manufacturing EPUs. Declaration of compliance is based on testing and documentation during the design, ground testing and flight testing of the EPU by the manufacturer or under the manufacturers’ guidance. Manufacturers of the EPUs are encouraged to review and incorporate appropriate standards and lessons learned from ground based systems as documented in SAE J2344 and EASA CRI F-58 (see Appendix X2). Electric aircraft may contain potentially hazardous level of electrical voltage or current. It is important to protect persons from exposure to this hazard. Under normal operating conditions, adequate electrical isolation is achieved through physical separation means such as the use of insulated wire, enclosures, or other barriers to direct contact. There are conditions or events that can occur outside normal operation that can cause this protection to be degraded. Some means should be provided to detect degraded isolation or ground fault. In addition, processes or hardware, or both, should be provided to allow for controlled access to the high voltage system for maintenance or repair. A number of alternative means may be used to achieve these electrical safety goals including automatic hazardous voltage disconnects, manual disconnects, interlock systems, special tools and grounding. The intention of all these means is either to prevent inadvertent contact with hazardous voltages or to prevent damage or injury from the uncontrolled release of electric energy. Lightning strikes are not addressed in this Standard Practice because LSA aircraft are limited to VMC flight only.1.1 This specification covers minimum requirements for the design and manufacture of Electric Propulsion Units (EPU) for light sport aircraft, VFR use. The EPU shall as a minimum consist of the electric motor, associated controllers, disconnects and wiring, an Energy Storage Device (ESD) such as a battery or capacitor, or both, and EPU monitoring gauges and meters. Optional onboard charging devices, in-flight charging devices or other technology may be included. 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 Electric Propulsion Units for Light Sport Aircraft

ASTM D7685-11 测定铁磁直列式,完全流通,感应传感器和非铁磁的磨损产物及航空衍生型和航空燃气机轮电机轴承的诊断标准操作规程

This practice is intended for the application of in-line, full-flow inductive wear debris sensors. According to (1), passing the entire lubrication oil flow for aircraft and aero-derivative gas turbines through a debris-monitoring device is a preferred approach to ensure sufficient detection efficiency. Periodic sampling and analysis of lubricants have long been used as a means to determine overall machinery health (2). The implementation of smaller oil filter pore sizes for machinery operating at higher rotational speeds and energies has reduced the effectiveness of sampled oil analysis for determining abnormal wear prior to severe damage. In addition, sampled oil analysis for equipment that is remote or otherwise difficult to monitor or access is not practical. For these machinery systems, in-line wear debris sensors can be very useful to provide real-time and near-real-time condition monitoring data. In-line full-flow inductive debris sensors have demonstrated the capability to detect and quantify both ferromagnetic and non-ferromagnetic metallic wear debris. These sensors record metallic wear debris according to size, count, and type (ferromagnetic or non-ferromagnetic). Sensors are available for a variety of oil pipe sizes. The sensors are designed specifically for the protection of rolling element bearings and gears in critical machine applications. Bearings are key elements in machines since their failure often leads to significant secondary damage that can adversely affect safety, operational availability, or operational/maintenance costs, or a combination thereof. The main advantage of the sensor is the ability to detect early bearing damage and to quantify the severity of damage and rate of progression of failure towards some predefined bearing surface fatigue damage limiting wear scar. Sensor capabilities are summarized as follows: In-line full flow non-intrusive inductive metal detector with no moving parts. Detects both ferromagnetic and non-ferromagnetic metallic wear debris. Detects 95% or more of metallic wear debris above some minimum particle size threshold. Counts and sizes wear debris detected. Fig. 1 presents a widely used diagram (2) to describe the progress of metallic wear debris release from normal to catastrophic failure. It must be pointed out that this figure summarizes metallic wear debris observations from all the different wear modes that can range from polishing, rubbing, abrasion, adhesion, grinding, scoring, pitting, spalling, etc. As mentioned in numerous references (1-11), the predominant failure mode of rolling element bearings is spalling or macro pitting. When a bearing spalls, the contact stresses increase and cause more fatigue cracks to form within the bearing subsurface material. The propagation of existing subsurface cracks and creation of new subsurface cracks causes ongoing deterioration of the material that causes it to become a roughened contact surface as illustrated in Fig. 2. This deterioration process produces large numbers of metallic wear debris with a typical size range from 100 to 1000 microns or greater. Thus, rotating machines, such as gas turbines and transmissions, which contain rolling element bearings and gears made from hard steel tend to produce this kind of large metallic wear debris that eventually leads to failure of the machines. In-line wear debris monitoring provides a more reliable and timely indication of bearing distress for a number of reasons:1.1 This practice covers the minimum requirements for an in-line, non-intrusive, through-flow oil debris monitoring system that monitors ferromagnetic and non-ferromagnetic metallic wear debris from both industrial aero-derivative and aircraft gas turbine engine bearings. Gas turbine engines are rotating machines fitted......

Standard Practice for In-Line, Full Flow, Inductive Sensor for Ferromagnetic and Non-ferromagnetic Wear Debris Determination and Diagnostics for Aero-Derivative and Aircraft Gas Turbine Engine Bearings

ANSI/NFPA 1125-2011 模拟火箭和高能火箭电动机的生产标准

1.1 Scope. 1.1.1* This code shall apply to the manufacture of model and high power rocket motors designed, sold, and used for the purpose of propelling recoverable aero models. 1.1.2 This code shall apply to the design, construction, and reliability of model and high power rocket motors and model rocket and high power motor-reloading kits and their components, and to the limitation of propellant mass and power. 1.1.3 This code shall not apply to the sale and use of the following: (1) Model rocket motors (covered by NFPA 1122, Code for Model Rocketry) (2) High power rocket motors (covered by NFPA 1127, Code for High Power Rocketry) 1.1.4* This code shall not apply to the manufacture, transportation, and storage of fireworks. 1.1.5 This code shall not apply to the manufacture, transportation, and storage of rocket motors by the United States military or other agencies or political subdivisions of the United States. 1.1.6 This code shall not apply to the assembly of reloadable model or high power rocket motors by the user. 1.1.7 This code shall not apply to the fabrication of model rocket motors or high power rocket motors by individuals for their personal use.

Code for the Manufacture of Model Rocket and High Power Rocket Motors

SAE AIR5373A-2010 地面支援设备中的燃料(汽油或柴油除外)

This SAE Aerospace Information Report (AIR) is intended as a source of comparative information and is subject to change to keep pace with experience and technical advances. This document describes currently used fuels which may be used in the future. Conventional gasoline and diesel fuels are intentionally omitted from this document. The purpose of this document is to provide basic information regarding fuels which can be used in aircraft ground support equipment. This document is recommended for use by those engaged in the design, selection, or maintenance of ground support equipment, and their fuel systems.

Fuels in Ground Support Equipment (Other Than Gasoline or Diesel)

SAE ARP6068-2010 燃气涡轮发动机测试设备振动测量

The test procedure per the applicable Engine Manual does require a vibration check for the low/intermediate and high speed rotor systems. Release of an engine with high vibrations can result in: On-wing vibration complaints, with subsequent troubleshooting; Rotorsystem failures; Premature engine removals Limits are provided for transient conditions and steady state data points. Troubleshooting recommendations are limited to verification of the proper signal input and tracking. This practice provides recommendations for: Correct cable and transmitter installation and connections; Calibration; Recorded data interpretation and data analysis

Gas Turbine Engine Test Facility Vibration Measurement

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 AIR5005A-2010 航空航天.商用航空器液压系统

This SAE Aerospace Information Report (AIR) has been compiled to provide information on hydraulic systems fitted to commercial aircraft. Data has been provided for the following aircraft types: a. Wide body jet airliners; b. Narrow body jet airliners; c. Turboprop/commuter aircraft; d. Business jet aircraft The airliners that have been included in this document are generally in operational service with either airlines or cargo operators. Information on aircraft that have been retired from in-service use has been included for reference purposes. No information is presented for aircraft that are currently being developed.

Aerospace - Commercial Aircraft Hydraulic Systems

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

SAE AIR4069B-2010 整体油箱的密封

This Aerospace Information Report (AIR) presents preferred practices for sealing and repairing integral fuel tanks, including rework of applied fuel tank seals. It addresses engineering designs for integral fuel tanks as they are currently found in practice; and this document discusses the most practical and conservative methods for producing a reliable, sealed system. Although this AIR presents practices for sealing of integral fuel tanks, the practices presented within this report are practices that are carried throughout sealing that include both pressure and environmental aircraft sealing.

Sealing of Integral Fuel Tanks

ASTM F2506-10 固定间距或地面可调轻型运动飞机的螺旋桨设计和试验的标准规范

1.1 This specification covers the establishment of the minimum requirements for the design, testing, and quality assurance of fixed-pitch or ground adjustable propellers for light sport aircraft. These propellers are used on light aircraft, and could be used with engines conforming to Practice F2339. 1.2 This specification is intended for use by manufacturers of propellers for light sport aircraft. 1.3 This specification does not address the airframe installation requirements for propellers. 1.4 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 to determine the applicability of regulatory limitations prior to use.

Standard Specification for Design and Testing of Fixed-Pitch or Ground Adjustable Light Sport Aircraft Propellers

GOST R ISO 8399-1-2010 航空航天学.产品附件连接.附件驱动和安装法兰(公制系列).第1部分:设计标准

Aerospace. Accessory connection to the product. Accessory drives and mounting flanges (Metric series). Part 1. Design criteria

GOST R ISO 8399-2-2010 航空航天学.产品附件连接及附件驱动和安装法兰(公制系列).第2部分:尺寸规格

Aerospace. Accessory connection to the product. Accessory drives and mounting flanges (Metric series). Part 2. Dimensions

SAE AIR4986A-2009 发动机静电气体通道监控

This document has been declared "CANCELLED" as of October 2009. By this action, this document will remain listed in the Numerical Section of the Aerospace Standards Index. Turbine engine malfunctions account for a substantial portion of the maintenance actions required to keep both fixed and rotary wing aircraft operational. Undetected incipient component failures can result in secondary engine damage and expensive unscheduled maintenance actions. Recent developments of electrostatic methods now provide the potential for the detection of foreign object ingestion and early detection of distress in gas path components. This SAE Aerospace Information Report (AIR) seeks to outline the history of the electrostatic technique and provides examples of state-of- the-art systems for both inlet and exhaust gas debris monitoring systems along with examples of most recent testing.

Engine Electrostatic Gas Path Monitoring