1、SAE AS*lbOb 92 = 7943725 0509707 li15 a a CAE Technical Standards Board Rules provide that: This report is published by SAE to advance the state of technical and engineering sciences. The use of this report is entirely voluntary, and its applicability and suitability for any particular use, includin
2、g any patent infringement arising therefrom, is the sole responsibility of the user.“ SAE reviews each technical report at least every tive years at which time it may be reaffirmed, revised, or cancelled. SAE invites your e written comments and suggestions. Copyright 1992 Society of Automotive Engin
3、eers, Inc. All rights reserved. Printed AEROSPACE STANDARD The Engineering Cocieiy e* =For Advancing Mobility Land Sea Air and Space INTERNATIONAL 400 Commonwealth Drive, Warrendale, PA 15096-0001 Submitted for recognition as an American National Standard -AL5 - AS1606 Issued 1992-09-15 GAS TURBINE
4、STARTER (JET FUEL STARTER) SPECIFICATION FOR E W ORD This SAE Aerospace Standard (AS) is a compilation of requirements extracted from various procurement specifications for similar equipment. The arrangement of this document is such that it might serve as an aid in the preparation of a gas turbine s
5、tarter (also referred to as a jet fuel starter) specification. Specific requirements or conditions are denoted “to be specified“ (TBS) to allow for use of actual application data or requirements. The “qualifying activity“ term used in this document is intended to be the organization that would typic
6、ally issue the actual specification (airframe manufacturer, engine manufacturer, or government agency). 1. SCOPE: This specification establishes the requirements for the (TBS) jet fuel starter for the (TBS) gas turbine engine used in the (TBS) aircraft. 1.1 Type: The jet fuel starter covered by this
7、 specification shall be designed to operate on jet fuel as a self-contained unit (subsequently called unit). in U.S.A. _-_lm- -_ - ._ .s SAE AS*IbOb 92 7743725 -0509708 051 = SAE AS1606 2, APPLICABLE DOCUMENTS: 2.1 Military Documents: The following documents form a part of this specification to the
8、extent specified herein. The applicable issue of governmental documents shall be the issue in effect on date of invitation for bids. 2.1.1 Specifications MI L-P- 116 MIL-C-3702 MIL-S-5002 MIL-H-5606 MIL-T-5624 MIL-L-6081 MIL-P-7105 MIL-S-7742 MIL-L-7808 MIL-C-8188 MI L- 1-8500 MIL-S-8879 MIL-L-23699
9、 MIL-E-25499 MI L-T-83 133 MI L-H-83282 2.1.2 Standards DOD-STD- 100 MIL-STD-129 MI L-STD- 130 MIL-STD-453 MIL-STD-461 MI L-STD-47 1 MIL-STD-480 MIL-STD-481 MIL-STD-704 MI L-STD-8 1 O MIL-STD-831 MIL-STD-889 Preservation , Method of Cable, Power, Electrical, Ignition, High-Tension Surface Treatments
10、 and Inorganic Coatings for Metal Surfaces of Weapons Systems Hydraulic Fluid, Petroleum Base, Aircraft Missile and Ordnance Turbine Fuel , Aviation, Grades JP-4, JP-5, and JP-5/JP-8 ST Lubricating Oil, Jet Engine Pi pe Threads , Taper , Aeronaut i cal Nat i onal Form, Symbol ANPT, General Requireme
11、nts for Screw Threads, Standard, Optimum Selected Series, General Speci fi cat i on for Lubricating Oil, Aircraft Turbine Engine, Synthetic Base, NATO Code Number 0-148 Corrosi on-Prevent i ve Oi 1 , Gas Turbi ne Engi ne Ai rcraft Synthetic Base Interchangeabi 1 i ty and Rep1 aceabi 1 i ty of Compon
12、ent Parts for Aerospace Vehicles Screw Threads, Controlled Radius Root with Increased Minor Diameter, General Specification for Lubricating Oi 1 Ai rcraft Turbine Engines Electrical Systems, Aircraft, Design and Installation of, General Speci fi cat i on for Turbine Fuels, Aviation, Kerosene Types N
13、ATO F-34 (JP-8) and Hydraulic Fluid, Fire Resistant, Synthetic Hydrocarbon Base, Aircraft, Metric, NATO Code Number H-537 NATO F-35 Engineering Drawing Practice Markings for Shipment and Storage Identification Marking of U.S. Military Property Inspection, Radiographic Electromagnetic Emission and Su
14、sceptibility Requirements for the Control of Electromagnetic Interference Maintainabil i ty Verification/Demonstration Evaluation Configuration Control - Engineering Changes Deviations and Waivers Configuration Control - Engineering Changes (Short Form) , Deviations and Waivers Aircraft Electric Pow
15、er Characteristics Environmental Test Methods and Engineering Guide1 ines Test Reports, Preparation of Di ssimi 1 ar Metal s -2- - SAE AS*lhOb 92 7943725 0509709 T98 SAE AS1606 2.1.2 (Continued) : MIL-STD-1523 Age Control of Age-Sensitive Elastomeric Material (For Aerospace Appl i cat ions) MIL-STD-
16、1595 Qualification of Aircraft, Missile and Aerospace Fusion We1 ders MIL-STD-1949 Inspection, Magnetic Particle MIL-STD-2175 Castings, Classification and Inspection of MIL-STD-6866 Inspection, Liquid Penetrant 2.2 Other Publications: The following documents form a part of this specification. indica
17、ted, the issue in effect on date of invitation for bids shall apply. Unless otherwise 2.2.1 Specification Control Drawing: MS20995 Wire, Safety or Lock MS33540 Safety Wiring and Cotter Pinning, General Practice for 2.2.2 Qual if i cation Agency Specifications: AFR 39-1 2 2.3 Commerci al Speci fi cat
18、 ions and Standards SAE AMS 2650 2.3 Definitions and Symbols: The applicable definitions and symbols used herein and in the model speci fi cat i on are as fol 1 ows : 2.3.1 2.3.2 2.3.3 2.3.4 2.3.5 2.3.6 QUALIFYING ACTIVITY: The qualifying activity is the activity which is responsible for the unit co
19、ntract. RATING: specified in the model specification. ESTIMATE: INITIAL YIELD: deformat i on has occurred. TRANSFER TIME: Transfer time is the time interval from the removal of the unit or component from one conditioning chamber to the insertion of the unit or component into another conditioning cha
20、mber, or the time interval from the removal of the unit or component from the conditioning chamber to the initiation of testing. START CYCLE: and acceleration of the load from zero rpm to unit cutout speed. A rating is the value of some characteristic of performance as An estimate is a predicted val
21、ue of performance. Initial yield is that point at which 0.2% permanent A start cycle shall consist of unit initiation (time zero) -3- - SAE AS*3606 92 W 79q3725 0509730 70T I SAE AS1606 2.3.7 2.3.8 2.3.9 2.3.10 2.3.11 2.3.12 2.3.13 2.3.14 2.3.15 2.3.16 2.3.17 MOTORING RUN: A motoring run shall consi
22、st of unit initiation (time zero) and acceleration of the load from zero rpm to a sustained speed. This point will occur when unit output torque equals the engine drag torque without engine light off. NO-LOAD CYCLE: output shaft. ZERO TIME: occurs. No-load is the operation of the unit without load o
23、n the Zero time is that time at which starting switch actuation CUTOFF: shaft. Cutoff is the speed at which the unit ceases to drive the output OVERRUNNING: means other than by energizing the unit turbine. MAXIMUM OPERATING SPEED: Maximum operating speed is defined as the highest speed obtained by t
24、he unit under the most severe temperature and alt i tude condition. Overrunning is the driving of the unit output shaft by some OVER SPEED: which causes the yield strength of the parts to be exceeded. PROOF SPEED: The proof speed is that speed above maximum operating speed which is used to nondestru
25、ctively test high speed rotating components. IMPACT TORQUE: Impact torque is the maximum torque resulting from initial engagement of the unit with the load. MAXIMUM TORQUE: Maximum torque is the highest torque value occurring after the initial impact torque occurs. MODEL SPECIFICATION: The model spe
26、cification referred to herein is defined as the vendor prepared document used to define the unit. Over speed is the rotation of high speed parts at a speed 3. REQUIREMENTS : 3.1 Operational Requirements: 3.1.1 Performance Characteristics: The unit shall meet the minimum performance requirements spec
27、ified herein. (If other than installed performance is intended, it shall be so stated.) The actual performance characteristics shall be specified in the model specification and shall be predicated on the use of production hardware. The minimum performance shown shall include adequate allowance for v
28、ariations due to controls, manufacturing tolerances, performance deterioration over the life of the unit, etc. Performance characteristics shall be based upon the use of MIL-T-5624 fuel s. 3.1.1.1 Output Torque: The minimum steady state and transient torque output shall be defined in the model speci
29、fication. Steady state torque shall not be less than that shown in Figure 2. Maximum steady state torque shall not exceed (TBS) . -4- SAE ASrLbOb 92 m 7943725 05097LL 646 m I Q SAE AS1606 3.1.1.2 3.1.1.3 3.1.1.4 3.1.1.5 3.1.1.6 Start Time: accessories described in Figure 3 to cutout speed in accorda
30、nce with the times shown in Figure 4. conditions of (TBS temperature and altitude points) shall be defined in the model specification. Performance Ratings: The unit performance shall be defined in the form of curves and a computer program which shall be part of the model specification. The curves sh
31、all include nominal and minimum performance. Performance shall be defined for operation of the unit under the following conditions in Table 1: The unit shall be capable of accelerating the engine and Calculated start times to cutout speed TABLE 1 - Performance Ratings Unit In1 et Air Fuel Temperatur
32、e Al ti tude Temperature Temperature (TBSI (TBSI (TBSI (TBSI -65 “F S.L. -65 “F -65 “F -40 “F S.L. -40 “F -40 “F +59 “F S.L. +59 “F +59 “F +160 9 S.L. +125 “F +130 “F +250 “F S.L. +125 “F +160 “F +160 “F 8000 ft +95 “F +loo 9 a. b. C, d. e. f. Unit transient output torque for (TBS) slug-ft2 test fly
33、wheel versus output shaft speed. (Sample shown as Figure 13) Gas generator speed versus time at no-load condition. (Sample shown as Figure 14a) Output speed versus time at no-load condition. Figure 14b) Unit exhaust gas temperature at discharge port versus time. Shown as Figure 15a) Unit airflow ver
34、sus speed. Torque transient at unit output drive versus running engagement speed showing maximum impact torque. (Sample shown as (Sample (Sample shown as Figure 15b) Fuel Consumption: The unit model specification shall define the units fuel consumption per start cycle for each operating condition in
35、cluding main engine motoring. Air Consumption: conditions shall be defined in the model specification. Exhaust Gas Temperature: The unit model specification shall define the maximum allowable exhaust gas temperature at the exhaust connection and shall specify the condition under which this occurs. U
36、nit airflow requirements for all extreme operating -5- SAE AS1606 3.1.1.7 Performance Deterioration: Performance deterioration of the unit shall not be more than (TBS) percent of the specification rating level after (TBS) start cycles and (TBS) hours motoring. calibration of the unit must meet or ex
37、ceed the minimum specification requirements. Performance during initial 3.1.2 Overhaul Life: The unit shall perform in accordance with the requirements of this document throughout (TBS) hours of overrunning (normal aircraft operating time), (TBS) start cycles, and (TBS) hours of motoring time. 3.1.3
38、 Unit Operation: 3.1.3.1 3.1.3.2 3.1.3.3 3.1.3.4 3.1.3.5 3.1.3.6 Start Cycle: consecutive start cycles, when exposed to the environmental conditions specified herein, with a maximum time interval of 60 s between the completion of one cycle and the initiation of the next cycle. No more than (TBS) sta
39、rt cycles shall be required within a 1 h period. The actual consecutive start cycle capability shall be specified in the model specification. Automatic Starting and Cutout: operation of a single switch or other device shall provide automatic unit operation from initiation to cutout. the initiation s
40、ignal being provided (i.e, due to windmilling or inadvertent unit rollover). The automatic starting and cutout provisions shall be specified in the model specification. Stopping: time during the start cycle without damage to the unit. The stopping provisions shall be specified in the model specifica
41、tion. Running Engagement: subjected to running engagements at any speed up to cutout. Motoring: similar load for periods up to (TBS) minutes duration followed by a normal start cycle within (TBS) minutes. consecutive motoring runs of lesser duration provided the total motoring time does not exceed (
42、TBS) minutes. No more than (TBS) minutes total motoring shall be required in any 1 h period. capability of the unit and any limitations shall be specified in the model specification. relationships exists, it shall be specified in the model specification. Minimum motoring speed at S.L. 59 OF shall be
43、 (TBS). The unit shall be capable of making at least (TBS) The unit shall be designed such that The unit shall not start without It shall be possible to terminate the starting cycle at any The unit shall suffer no detrimental effects when The unit shall be capable of motoring the aircraft engine or
44、It shall be possible to make The actual motoring If a motoring speed/motoring time allowed Altitude Starts: The unit shall be capable of provid performance per Figure 7, when operated in the flight at inlet and exhaust conditions of Zone A of Figure 6 ng min reg i me mum of Figure 8 -6- SAE AS*lbOb
45、92 7943725 0509733 419 SAE AS1606 3.1.4 Unit Characteristics: 3.1.4.1 Unit Starting System: The unit shall be equipped with a device that will drive the gas generator to self-sustaining speed. The energy source to be suppl ied by the airframe can be electrical y hydraul icy pneumatic or a combinatio
46、n of these. The unit shall be capable of making a minimum of (TBS) consecutive start cycles throughout the operating envelope when supplied with the energy source specified in the model specification. a. Electric: A (TBS) battery with the electrolyte maintained between (TBS) OF and (TBS) OF. Cable a
47、nd relays with total resistance of (TBS) ohm. b. Hydraul i c : (1) Accumulator of (TBS) volume. (2) Precharge pressure of dry nitrogen at gas temperature of (TBS) psig. (3) Charge pressure of (TBS) psig stabilized at (TBS) OF gas temperature. (4) Fluid used: (TBS) (5) Line and valve losses. (a) Supp
48、ly per Figure (TBS) (b) Return per Figure (TBS) Return reservoir pressure at (TBS) psig. (6) c Pneumat i c : (1) Pneumatic bottle with a volume of (TBS) charged to (TBS) psi at stabilized gas temperature of (TBS). (2) Supply line and valve losses per Figure (TBS) (3) Gas used. Dry air or nitrogen. C
49、utoff of the initiating device shall be automatically controlled by a signal from the unit, which will be specified in the model specification. Input power requirements from the aircraft electrical system shall be specified in the model specification. The transient performance of 3.1.1.2 and 3.1.1.3 shall include time from the initiation of the starting of the unit. -7- SAE AS1606 3.1.4.2 Compressor and Turbine System: 3.1.4.2.1 Mass Moment of Inertia: The mass moment of inertia of the entire gas generator rotating system referred to the gas generator initiating de
