SAE ARP 1507A-1997 Helicopter Engine Airframe Interface Document and Checklist《直升机发动机 机身接口文档和清单》.pdf

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1、SAE Technical Standards Board Rules provide that: “This report is published by SAE to advance the state of technical and enginee ring sciences. The use of this report is entirelyvoluntary, and its applicability and suitability for any particular use, including any patent infringement arising therefr

2、om, is the sole responsibility of the user.”SAE reviews each technical report at least every five years at which time it may be reaffirmed, revised, or cancelled. SAE invit es your written comments and suggestions.Copyright 1997 Society of Automotive Engineers, Inc.All rights reserved. Printed in U.

3、S.A.QUESTIONS REGARDING THIS DOCUMENT: (412) 772-8510 FAX: (412) 776-0243TO PLACE A DOCUMENT ORDER: (412) 776-4970 FAX: (412) 776-0790400 Commonwealth Drive, Warrendale, PA 15096-0001AEROS PACE RECOMMENDED PRACTICESubmitted for recognition as an American National StandardARP1507 RE V. AIssued 1985-0

4、9Reaffirmed 1991-05Revised 1997-06Superseding ARP1507H elicopter E ngine /A irframe I nterface D ocument and C hecklistFOREWORDChanges in this revision are format/editorial only.TABLE OF CONTENTS1. SCOPE . 32. REFERENCES . 32.1 Recommendation 33. HELICOPTER ENGINE/AIRFRAME INTERFACE DOCUMENT AND CHE

5、CKLIST . 43.1 General Description 43.1.1 Engine Description 43.1.2 Engine Subsystem Description . 43.2 Engine Functional Characteristics 43.2.1 Performance, Steady State . 43.2.2 Starting and Operating Envelope 53.2.3 Operating Attitudes . 53.2.4 Mechanical and Thermal Limits 53.2.5 Operating Flight

6、 Limit Loads . 53.2.6 Vibration Limits 53.2.7 Control System . 53.2.8 Fuel System 53.2.9 Oil System . 83.2.10 Starting System . 83.2.11 Compressor Air Bleed . 83.2.12 Engine Heat Rejection and Cooling 113.2.13 Electrical System 113.2.14 Air Induction System . 113.2.15 Exhaust System 11SAE ARP1507 Re

7、vision A- 2 -TABLE OF CONTENTS (Continued)3.2.16 Engine Condition Monitoring and Diagnostics 113.3 Engine Physical Characteristics 113.3.1 Weight . 113.3.2 Engine Dimensions . 113.3.3 Engine Mounts 123.3.4 Mass Moments of Inertia . 123.3.5 Output Shaft 123.3.6 Accessory Drive 123.3.7 Fuel System and

8、 Control System 123.3.8 Oil System . 123.4 Drawings . 143.4.1 Installation Drawing . 143.4.2 Electrical System Drawing 153.5 Interface Checklist . 16APPENDIX A INTERFACE CHECKLIST . 17SAE ARP1507 Revision A- 3 -1. SCOPE:This SAE Aerospace Recommended Practice (ARP) provides a guide for the preparati

9、on of a Helicopter Engine/Airframe Interface Document and Checklist. This document and checklist is intended to provide complete relevant information on the characteristics, performance, and engine interfaces. Of most importance is the identification of the data and the location of data to assure th

10、at the engine manufacturer and the airframe manufacturer supply information that can be easily located by either manufacturer.2. REFERENCES:2.1 Recommendation:The Helicopter Engine/Airframe Interface Document and Checklist should be organized into five sections: a general description of the engine a

11、nd the engine subsystems, engine functional characteristics, engine physical characteristics, installation drawings, and interface checklist.During the preparation of the interface document and checklist, the following documents should be evaluated for applicability:AS681 Gas Turbine Engine Steady S

12、tate Performance Presentation for Digital Computer ProgramsARP704 Helicopter Engine - Rotor System CompatibilityARP721 Turbine Drive Shaft ConnectionAIR947 Engine Erosion Protection (Helicopter)ARP949 Turbine Engine Starting System Design RequirementsAIR984 Air Bleed Objective for Helicopter Turbine

13、 EnginesARP996 Cooling of Turbine Engines in HelicoptersAIR1087 Aircraft Accessory Drag Torque During Engine StartsAIR1160 Aircraft Engine and Accessory Drives and Flange StandardsAIR1191 Performance of Low Pressure Ratio Ejectors for Engine Nacelle CoolingARP1257 Gas Turbine Engine Transient Perfor

14、mance Presentation for Digital Computer ProgramsAIR1262 Aircraft, Fire Protection for Helicopter Gas Turbine Powerplant and Related Systems InstallationsSAE ARP1507 Revision A- 4 -2.1 (Continued):ARP1279 Standard Indoor Method of Collection and Presentation of the Bare Turboshaft Engine Noise Data,

15、for Use in Helicopter InstallationsAIR1286 Helicopter and V/STOL Aircraft Noise Measurement ProblemsAIR1289 Evaluation of Helicopter Turbine Engine Linear Vibration EnvironmentARP1420 Gas Turbine Engine Inlet Flow Distortion GuidelinesAIR1423 Electromagnetic Compatibility on Gas Turbine Engines for

16、Aircraft PropulsionARP1587 Aircraft Gas Turbine Engine Monitoring System GuideARP1702 Defining and Measuring Factors Affecting Helicopter Turbine Engine Power Available3. HELICOPTER ENGINE/AIRFRAME INTERFACE DOCUMENT AND CHECKLIST CONTENTS:3.1 General Description:3.1.1 Engine Description: The engine

17、 description should include the air flow class and a general identification of the compressor configuration, combustor configuration, number of turbine stages, exhaust configuration and output shaft configuration with direction of rotation and speed. If the engine has a reduction gearbox, the speed

18、reduction should be addressed. When an engine uses modular construction, the modules should be described. An engine cutaway should be provided.3.1.2 Engine Subsystem Description: Each engine subsystem such as fuel, control, oil, electrical, starting, compressor air bleed, induction, exhaust, conditi

19、on monitoring, and diagnostics should be described. The descriptions should address the components in the subsystems, general operating characteristics, and unique features. Subsystems schematics should be provided.3.2 Engine Functional Characteristics:3.2.1 Performance, Steady State: A definition o

20、f engine ratings such as takeoff power, 2 minute power, 30 minute power, etc., must be included. Tables are recommended which include engine performance at standard, sea level, static conditions at minimum rated delivered shaft power, rated delivered shaft speed, maximum specific fuel consumption an

21、d measured gas temperature. Performance estimating procedures should be explained or adequate tables or figures provided. If the primary source of estimated performance is a computer program, the computer program should be described.SAE ARP1507 Revision A- 5 -3.2.2 Starting and Operating Envelope: T

22、he engine starting and operating envelope with any associated engine limitations necessitated by ambient conditions or flight speed must be described. Figure 1 depicts a typical starting and operating envelope. Starting times as a function of ambient temperatures must be addressed, and it is recomme

23、nded that they be graphically depicted as a function of ambient temperature.3.2.3 Operating Attitudes: The engine capability for continuous attitude operation and transient attitude operations must be described.3.2.4 Mechanical and Thermal Limits: The gas generator speed, power turbine speed, output

24、 shaft torque and measured gas temperature limits at rated powers and during transients must be stated.3.2.5 Operating Flight Limit Loads: The engine flight limit loads must be identified. Figure 2 depicts a typical limit load envelope.3.2.6 Vibration Limits: The engine limits (engine induced and ai

25、rcraft induced) must be identified and the installation drawing must identify the vibration pickup location. Steady state and transient limits provided over applicable ranges should be identified with the definitions for steady state transients and frequency/spectral range.3.2.7 Control System: The

26、control system philosophy control modes and characteristics should be completely described in paragraph 3.1.2. Control system lever(s) minimum and maximum torque required to rotate the levers should be stated. Information must be provided on the lever rotation dwell bands. If the control system uses

27、 electrical inputs, the signal characteristics must be defined. Components may be added to the control system to enhance stability, i.e., stability accumulators. These components must be coordinated between the engine manufacturer and the helicopter manufacturer and the location, allowable loads, et

28、c., shown on the installation drawing. Engine transient response characteristics should be described based upon control lever movement.3.2.8 Fuel System:a. The fuels for normal use and special use must be identified with any necessary restrictions. Fuel additives if approved should be identified.b.

29、Maximum fuel flow should be identified.c. Fuel inlet conditions should be identified which address fuel system assist from the helicopter throughout the operating envelope, ground and air starting, vapor/liquid ratio capability and any limitations on fuel inlet pressure at/after engine shutdown.SAE

30、ARP1507 Revision A- 6 -FIGURE 1 - Starting and Operating EnvelopeSAE ARP1507 Revision A- 7 -FIGURE 2 - Externally Applied ForcesSAE ARP1507 Revision A- 8 -3.2.9 Oil System:a. The oil for normal use must be identified with any necessary restrictions.b. Oil system operating pressures and temperature m

31、ust be identified throughout the operating envelope and the location of sensors must be stated.c. Oil system flow and cooling requirements must be identified if the engine requires a helicopter furnished engine oil cooling.d. Oil consumption rate and oil flow must be identified if the engine require

32、s a helicopter furnished engine oil tank.e. Oil system vent requirements including location, maximum flow rates, and vent pressure restriction limits must be identified.f. Oil filter location and characteristics such as type of filter, filtration capability, bypass or impending bypass capability, et

33、c., should be described.3.2.10 Starting System: The required starter torques and drive speeds will be stated and shown in a figure, such as Figure 3. The figure should include engine drag, breakaway torque, engine accessory drag, and customer accessory gearbox drag. The figure should show the effect

34、s of ambient temperatures and altitudes and alternate fuels. A figure should be included which shows the effect on starting time caused by ambient temperature and altitude (Figure 4). The maximum effective mass moment of inertia of engine rotating parts to be rotated by the starter, referred to the

35、starter drive, and the speed ratio between the starter pad and the driven rotor system must be stated. The torsional spring constant for the engine starting drive system at the starter drive pad must be stated. The maximum backlash of the starting drive system in radians at the starter drive pad sho

36、uld be identified.3.2.11 Compressor Air Bleed: If a compressor air bleed source is available, the mounting type, location, dimensions and limit loads must be identified. The maximum permissible air bleed must be identified. The air bleed purity must be stated. The responsibility for limiting the air

37、 bleed must be established.SAE ARP1507 Revision A- 9 -FIGURE 3 - Starting Torque and Speed Requirements(Sea Level Static Conditions)SAE ARP1507 Revision A- 10 -FIGURE 4 - Engine Ground Starting Time Versus AmbientAir Temperature - (Static Sea Level to 5 km)SAE ARP1507 Revision A- 11 -3.2.12 Engine H

38、eat Rejection and Cooling:a. The engine heat rejection and cooling should be described as defined in ARP996.b. If there are engine component limiting temperatures, the components and their temperature limits will be stated and the installation drawing will identify the thermocouple location and type

39、.3.2.13 Electrical System: The electrical system must be described on the installation drawing. Individual engine component power requirements and power characteristics from the helicopter and requirement duration must be identified. The engine electrical output signals to the helicopter, signal cha

40、racteristics and the signal duration must be identified.3.2.14 Air Induction System:a. The air induction system should be described, especially such features as inlet connection and any integral protection from foreign objects or required foreign object protection from the helicopter.b. The air indu

41、ction anti-icing system should be described, especially system function with electrical supply failure.c. Inlet distortion limits should be identified.3.2.15 Exhaust System: The exhaust connection mounting type, location, dimensions, and limit loads must be identified. If an exhaust centerbody is re

42、quired, the mounting type, location, dimensions, and limit loads must be identified. The engine manufacturer should identify a recommended exhaust configuration which is compatible with engine performance.3.2.16 Engine Condition Monitoring and Diagnostics: The condition monitoring and diagnostics ca

43、pabilities should be described. If component power requirements exist, they should be identified in paragraph 3.2.13, Electrical System. The instrument range, system accuracy, time response, and electrical characteristics for each parameter that is required for safe engine operation and operation wi

44、thin established operating limits shall be presented in the Helicopter Engine/Airframe Interface Document and Checklist.3.3 Engine Physical Characteristics:3.3.1 Weight: The engine dry weight must be stated. It is recommended that the weight of residual fuel and oil be identified when the engine is

45、in a horizontal attitude. If there are components which may be furnished with an engine, such as accumulators, fuel flow meters, etc., it is suggested that the component part number and weight be stated.3.3.2 Engine Dimensions: The engine dimension must be on the installation drawings which must be

46、a part of the Helicopter Engine/Airframe Interface Document and Checklist.SAE ARP1507 Revision A- 12 -3.3.3 Engine Mounts: Any engine mounting considerations should be stated. Specific information on mount locations, dimensions and static, dynamic and limit loads must be identified. It is recommende

47、d that this information be on the installation drawing.3.3.4 Mass Moments of Inertia: The following will be stated:a. The mass moment of inertia of the complete dry engine about three mutually perpendicular axes with the origin at the center of gravity.b. The mass moment of inertia of each engine ro

48、tor system about the resultant rotational axis, together with the effective direction of rotation of the inertia and the direction and location of the resultant rotational axis. For engines with geared rotor systems, the shaft to which all inertias of each rotor system have been algebraically referr

49、ed will be stated.c. The mass moment of inertia of the complete power output system (including the reduction gear train) referred to the output shaft speed.3.3.5 Output Shaft: The output shaft configuration, i.e., internal spline, external spline, etc., must be stated and the direction of rotation must be stated. Specific information on the spline pad location and limit loads must be identified on the installation drawing. Any special consideration such as wetted spline oil control or angular misalignment should be identified.3.3.6 Accessory Drives: A table similar to Table 1 must be includ