1、MIL-85573 28 W 797790b 0207126 T 9 MIL-P-85573(AS) 15 November 1983 1. 1. MILITARY SPECIFICATION POWER UNIT AIRCRAFT, AUXILIARY, GAS TURBINE GENERAL SPECIFICATION FOR This specification is approved for use by the Naval Air Systems Command, Department of the Navy, and is available for use by all Depa
2、rt- ments and Agenc*ies of the Department of Defense. SCOPE 1 Scope, This specification establishes the performance, operating characteristics, design features, detailed interface configuration definitions, and installation envelopes for a gas turbine auxiliary power unit (APU). This specification a
3、lso establishes the demonstrations, tests, reports, inspection procedures, and other data required for satisfactory completion and acceptance, hy the Using Service, of the Preliminary FTight Rating Tests (PFRT) and the Verification Tests (VT) for APUs. Further, this specification identifies the test
4、s, procedures and data required for satisfactory completion of the Acceptance Tests (AT) of each production unit. Notwithstanding the requirements for test verification of individual points of performance or operating characteristics of the APUs covered by this specffication for purposes of PFRT, VT
5、, or AT; the manufac-turer/contractor shall continue to be fully responsible for all features, characteristics, and performance of the APU throughout the environmental conditions and operating envelope, to the extent required by the applicable contract. This specification also establishes the conten
6、t and format to be used by the contractor for the preparation of the model specification, 1.2 Components. The APU defined in this specification shall include, but not be limited to, the following components furnished as part of and qualified Beneficial comments (recommendations, additions, deletions
7、) and any pertinent data which may be of use in improving this docu- ment should be addressed to: Engineering Specifications and Standards Department (Code 93), Naval Air Engineering Center, Lakehurst, NJ 08733, by using the self-addressed Standardiza- tion Document Improvement Proposal (DD Form 142
8、6) appearing at the end of this document or by letter. FSC 2840 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-with the APU: Intake shroud, power section, load compressor, gearbox, control system, fuel system, ignition system, oil system, starter mo
9、tor and exhaust duct 2 , APPL I CAGLE DOCUMENTS 2,l Government documents. Z,l,l Specifications and standards. Unless otherwise specified, the following specifications and standards of the issue listed in that issue of the Department of Defense Index of Specifications and Standards (DoDISS) specified
10、 in the model specification form a part of this specification to the extent specified herein. SPECIFICATIONS FEDERAL TT-S-735 Standard Test F1 uids; Hydrocarbon MILITARY MIL-C-3702 MIL-T-5544 MIL-E-5607 MIL-T-5624 MIL-C-7024 MIL-S-7742 MIL-L-7808 MIL-98879 MIL-1-18802 MIL-L-23699 MIL-H-25579 MIL-1-2
11、7686 MIL-C-38373 MIL-H-46855 MIL-W-81381 MIL-T-83133 Cable, Power, Electrical, Ignition, High Tension Thread Compound, Antiseize, Graphite-petrolatum Engine, Gas Turbine, Preparation for Storage and Turbine Fuel, Aviati on, Grades JP-4 and JP-5 Calibrating Fluid, Aircraft Fuel System Components Scre
12、w Threads, Standard, Optimum Selected Series; Lubricating Oil, Aircraft Turbine Engine, Screw Threads, Control led Radius Root with Shipment of, Process for General Specification for Synthetic Base Increased Minor Diameter, General Specification for Fuel and Oil Lines, Aircraft, Installation of Lubr
13、icating Oil, Aircraft Turbine Engines, Synthetic Base Hose Assembly, Tetrafluoroethylene, High Temperature Medi um Pressure, General Requirements for Inhibitor, Icing, Fuel System Cap, Fluid Tank Fi 1 ler Human Engineering Requirements for Mi 1 i tary Wire, Electric, Polyimide-insulated, Copper and
14、Turbine Fuel, Aviation Kerosene Type, Grade JP-8 Systems, Equipment and Faci 1 i ties Copper Al 1 oy I O I 2 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-P-85573 28 W 9999906 0207128 3 W MIL-P-85573(AS) STANDARDS MILITARY DOD-STD-100 MIL-STD-1
15、30 MIL-SlD-210 MIL-STD-454 MIL-STD-461 MIL-STD-462 MIL-STD-470 M.1 L-STD-704 MIL-STD-785 MIL-STD-810 MIL-STD-838 MIL-STD-882 MIL-STD-889 MIL-STD-1390 MIL-STD-1472 MIL-STD-1523 MIL-STD-1629 MS 3336 MS 14169 MS 14184 MS 21209 MS 24476 MS 33514 MS 33537 . MS 33540 MS 33587 MS 33649 Engineering Drawing
16、Practices Identification Marking of U.S. Military Property Cl imatic Extremes for Mi 1 i tary Equipment Standard General Requirements for Electronic Electromagnetic Emission and Susceptibility Equipment Requirements for the Control of Electromagnetic Interference Measuremsnt of Systems and Equipment
17、s) Electromagnetic Interference Characteristics, Maintainability Program Requirements (For Aircraft Electric Power Characteristics Reliability Program for Systems and Equipment Deve1 opmen t and Product i on Environmental Test Methods Lubrication of Military Equipment System Safety Program Requireme
18、nts Dissimilar Metals Level of Repair Human Engineering Design Criteria for Mi Age Control of Age-Sensi tive Elastomeric Procedures for Performing a Failure Mode Systems, Equipment and Facilities and Criticality Analysis 1 i tary Material , Effects Accessory Drives Aircraft Engine, Reference Chart C
19、ircular Spline compressors, including number of stages, variable geometry provisions, acceleration bleeds; combustor type rncluding method of fuel injection; turbine components including number of stages, cooling 5 Provided by IHSNot for ResaleNo reproduction or networking permitted without license
20、from IHS-,-,-provisions; exhaust duct; control system; gearbox provisions; type of lubrication and scavenge system; start motor; starting and ignition systems; number and location of main bearings; instrumentation and performance indicating provisions, The performance ratings shall be specified in t
21、he model specificatian in accordance with tables I and II. A detailed APU characteristics summary shall be included as shown in table III. Terms, symbols, and their definitions shall be in accordance with section 6. 3.1.1 Item diagrams. Item diagrams shall be provided for the fuel, ignition, lubrica
22、tion and control systems, gas flow path (see 3,2.1.2), basic assemblv and other systems as required by the Using- Service. Item ciiagrams shall be“ attached to the model specification in the form of figures. 3.1.2 Interface definition. The interface requirements include all physica installation and
23、performance requirements necessary for instal lation of the APU, All interface definitions shall require approval of the Using Service prior to incorporation into the APU dssign, In addition, all interfaces sha be as shown on the APU configuration and envelope drawing or in the text describing the a
24、pplicable functional system. 3,1,2,1 Drawings. The following drawings, as figures, shall form a part of the model specification. Reduced size copies of these figures shall be included in the model specification, a, APU configuration and envelope figure, This drawing shall include detailed profiles i
25、n all planes to show and identify the physical interface features of the APU. The drawing shall show mounting details and tolerances for the APU and all installation items, clearances for installation and 1 11 removal of accessories and components subject to separate removal, access for adjustments
26、and other maintenance functions and the center of gravity of the dry APU, This drawing shall show the maximum space required by the APU including tolerances and dimensional changes due to manufacturing, thermal effects, vibration, and operating and externally applied loads. and identify all external
27、 electrical circuit requirements and installation interface connection details. . . b, Electrical installation connection figure. This drawing shall show 3,1,2,2 Mock-up, A full scale mock-up shall be prepared in accordance with the applicable contract. 3.1.2.3 Installation interfaces. APU features
28、affecting installation interfaces shall be established in the model specification. Changes (additions, deletions or modifications) shall be submitted to the Using Service for approval only after coordination between the interfacing contractors as required by the applicable contract, 3,1.2,4 Mass mom
29、ent of inertia. The maximum effective mass moment of inertia (slug-ft2) of the complete dry APU about three mutually perpendicular axes 6 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-with the origin at the center of gravity shall be specified in t
30、he modei specification. The maximum effective mass moment of inertia (slug-ftz) about the resultant rotational axis, together with the direction of rotation when viewed looking forward from the exhaust, shall also be specified. 3.1.2.5 Externally applied forces. The APU, mounted in the mounting prov
31、isions of 3.1.2.6, shall function satisfactorily under the conditions of figure 1 without permanent deformation and shall operate satisfactorily thereafter. The APU shall also not fail when subjected to static loads equivalent to 1.5 times those values but need not operate satisfactorily thereafter.
32、 The 1 imit loads shall be based on a weight factor consisting of the dry weight of the APU, increased by the specific weight allowed for all APU mounted accessories and operating fluids. When airframe components are supported by the APU, the weight of these components shall be included in the weigh
33、t factor. A report shall be submitted containing a detailed structural analysis of the entire APU with regard to its capability to withstand the loads specified in this paragraph and 3.1.2.5.1 (see 4.5.4.3 and 4.6.6.5). 3.1.2.5.1 Gyroscopic moments. At all speeds up to at least maximum allowable ste
34、ady-state rotor speed, the APU shall operate satisfactorily when a gyroscope moment is imposed under the following (see 4.6.6.7): a. Uncontrolled flight. A steady angular velocity of 3.5 radians per second in any axis in a plane perpendicular to the rotor axis, cmbined with a vertical load factor of
35、 either +lg or -1g for a total period of 15 seconds. b. Controlled flight. A steady angular velocity of 1.4 radians per second in any axis in a plane perpendicular to the rotor axis, and the maximum load factor shown in figure 1, for infinite cyclic life. 3.1.2.6 APU mounts. The number, type, locati
36、on, interface dimensions, and the maximum allowable load limits at each individual attachment point shali be shown on the APU configuration and envelope figure (see 4.5.4.3 and 4.6.6.5). 3.1.2.6.1 Ground handling mounts. Ground handling mounts shall be provided on the APU to support the weight of th
37、e APU increased for all APU mounted accessories and operating fluids. The handling mounts shall withstand loads of 4g axial, 2g lateral, and 39 vertical, without permanent deformation, based on the weight of the APU defined above. The location and dimensions for the individual ground handling mounts
38、 shall be shown on the APU configuration and envelope figure. If adapters are necessary, these will be designed and provided by the manufacturer. The APU shall incorporate means for lifting or hoisting and shall be capable of resting on a level surface without damaging lines, cables, fittings, or co
39、mponents attached to the surface of the APU. 3.1.2.7 Pads and drives. Pads and drives suitable for mounting and driving APU components and aircraft accessories shall be in accordance with the basic configuration and rating requirements specified in the model specification and presented as shown in t
40、able IV. The drive system shall be capable of 7 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-P-85573 28 W 997990b 0207133 7 m MIL-P-85573(AS) simultaneous operation of all the drives when each drive is subjected to the maximum permissible torq
41、ue or power rating specified for the individual drive, If drive splines are lubricated, they shall either be positively lubricated with APU oil, or incorporate provisions for non-metal lic shaft-couplings as described in MS 14169 or MS 14184, depending upon the interface of the shaft coupling to the
42、 drive. Complete dimensions and details of the drive pads including the clearance envelopes and alignment requirements shall be shown on the APU configuration and envelope figure. No part of the gearbox shall prevent independent removal of any one component mounted on these drives , Pads and drives
43、shall conform to the appropriate MS standard listed on MS 3336, 3,1,2,8 Heat rejection and cooling, (see 4.4.1) 3.1.2.8,l Limiting temperatures, The maximum operating surface temperature of the APU and of al 1 its components and accessories external to the APU, shall be specified in the model specif
44、ication. These temperatures shall not be exceeded when surrounded by compartment air under the following conditions: a, Continuous operation at rated loads with the compartment air either at 2500F (121OC) or at the maximum sea level hot atmosphere temperature plus the ram air temperature rise at the
45、 maximum ram pressure ratio specified for APU operation, whichever is greater. b, In-flight shutdown from the most adverse condition and continued soaking with the compartment inlet air at the maximum stagnation temperature, The most adverse condition is the operating load that releases the most hea
46、t into the APU compartment. This condition shall be specified in the model specification. c, Ground shutdown with compartment air at 25OoF (121OC) , Cooling air shall be provided by the APU, if necessary, to meet item a. If required, a fan drive shall be provided and its characteristics shall be spe
47、cified in the model specification. No APU component or accessory shall require special cooling (e.g., forced convection, refrigeration or rotor rotation) to meet i tems “b“ and “c“ above. 3,1,2,8,2 Compartment temperature. The APU shall provide for compartment cooling such that the compartment air t
48、emperature during ground operation shall not exceed 25OOF (121OC) under the hot atmosphere condition, Compartment temperature transients after shutdown shall not exceed 4OOOF (204OC). Surface temperatures of the APU and its accessories shall not exceed 50OOF (26OOC) during normal operation, with the
49、 exception of the exhaust duct, 3.1,2.8,3 Oil flow and heat rejection. The performance of the oil system, the associated cooling provisions and the cooling requirements shall be specified in the model specification, The oil flow, heat balance and heat rejection data based upon the maximum limiting zone temperatures of 3.1.2.8.1 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I MIL-P-85573(AS) a shall be speci
