NAVY MIL-B-81365-1966 BLEED AIR SYSTEMS GENERAL SPECIFICATION FOR《一般规格排气系统》.pdf

1、MIL-B-81365 (WP) 4 April 1966 MILITARY SPECIFICATION BZEED AIR SYSTEMS, GENEWL SPECIFICATION FOR This speaificatiomhas been approved by the Bureau of Naval Weapons, Department of the Navy. 1. SCOPE 1.1 his specification covers bleed air systems for turbo-jet, turbo-prop, and turbo-shaft aircraft, 2.

2、 APPIjfCABLE DOCUMENTS 2, i Government documents normally furnished - The following documents, of the issue in effect on date of invitation for bids or request for pro- pow, form a part of this specification to the extent specified herein. SPECIFICATIONS Military MIL -C -5 O 15 Connectors; Electrica

3、l, “AN“ Type MIL-W-5 088 Wiring, Aircraft, Installation of MIL-E-5272 - Environmental Testing, Aeronautical and Associated Equipment, General Specifica- tion for MIL-C -6021 Castings, Classification and Inspection of MIL -E -6 05 1 Electrical-Electronic System Compati - bility and Interference Contr

4、ol Require- - ments-for Aeronautical Weapon System Electric Equipment, Aircraft, Selection MIL-E -7080 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-B-81365 (WP) SPECIFICATIONS Military (Continued) MIL-F-7179 MIL-S-7 742 MIL-S-8879 MIL-C-27 536

5、 STANDARDS . Military MIL-STD- 210 MIL-STD-704 MS24563 MS33586 PUBLICATIONS Finishes and Coatings, General Specifi- cation for Protection of Aircraft and Aircraft Parts Screw Threads, Standard, Optimum Selected Series: General Specification for Screw Threads, Controlled Radius Root with increased Mi

6、nor Diameter, General. Specification for Coupling, Clamp, Grooved, V-Band Climatic Extremes for Military Equip- ment Electric Power, Aircraft, Characteris- tics and Utilization of Dimensions, Profile, V-band Coupling Flanges, Design Standard for Metals, Definition of Dissimilar Naval Weapons Require

7、ments WR-62 Specifications and Standards; Use of (When requesting applicable documents, refer to both title and number. Copies of unclassified documents may be obtained from the Commanding Officer, Naval Supply Depot (Code 10511, 5801 Tabor Avenue, Philadelphia, Pennsylvania 19120, Requests for copi

8、es of classified documents should be addressed to the Naval Supply Depot, via the cognizant Government inspector. /- 2 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-B-81365 (WP) 3. REQUIREMENTS 3.1 Precedence - In case of conflict between this

9、specification and a detail specification, the requirements of the detail specification shall take pre- c edenc e. 3.2 Selection of specifications and standards - Specifications and standards for necessary commodities and services not specified herein shall be selected in accordance with WR-62. 3.2.1

10、 Standard parts - MS and AN standard parts shall be used. They shall be identified on the drawings by their part numbers. 3.3 Materials - Materials shall conform to applicable specifica- tions and shall be as specified herein and on applicable drawings. 3.3.1 Metal parts - All-metal parts shall be o

11、f a corrosion resistant material or treated in a manner to render them adequatly resistant to corrosion due to salt spray, or atmospheric conditions likely to be met by aircraft on carrier (shipboard) duty. Parts shall be protected in accordancewith MIL-F-7179. Magnesium alloy shall not be used. 3.3

12、.1.1 Dissimilar metals - Unless suitably protected against electro- lytic corrosion in accordance with MIL-F-7179, dissimilar metals shall not be used in intimate contact with each other. Dissimilar metals are defined in MS 33586. 3.3.1.2 Castings - All castings shaii be Class I in accordance with M

13、IL-C-6021. 3.3.2 Nonmetallic materials - Any nonmetallic material that is ad- versely affected by salt spray, compressor air, environmental or operating tem- peratures, and aircraft operating atmospheres shall not be used. 3.4 Design and construction - 3.4.1 Atmospheric design conditions - The syste

14、m design tempera- ture conditions shall be based on the standard cold and hot atmospheres presented in MIL -STD -21 O. 3.4.2 Air and pressure source - The engine compressor air shall be used as the air and pressure source for the system. 3 _- Provided by IHSNot for ResaleNo reproduction or networkin

15、g permitted without license from IHS-,-,-MIL-B-81365 16 9977706 0204548 T W MIL- B -81365 (WP 3.4.3 Engine overheat prevention - Operation of the system shall not cause overheating of the engine or engine exhaust nozzle. 3.4.4 Selection and installation of electrical equipment - Electrical equipment

16、 shall be selected and installed in accordance with MIL-W-5088, MIL-E-6051, and MIL-E-7080. Where equipment is subject to removal for in- spection and rewiring, AN connectors conforming to MIL-C-5015 shall be used. 3.4.5 Input power requirement6 - The electrical system shall meet the applicable requ

17、irements of MIL-STD-704, and shall be capable of operating satisfactorily throughout the entire variations of voltages and frequencies per- mitted therein. Installation of all wiring external to the electrical components shall be in accordance with MIL-W-5088. 3.4.6 Insulation - The insulation and h

18、eat shielding of the bleed air system components and ducting shall be such that no structural member of the aircraft is raised to a temperature above its designed allowable because of bleed air system operation. 3.4.7 System design - The system shall be as simple and foolproof as possible with respe

19、ct to design, operation, inspection, and maintenance, The bleed air system and its components shall be designed to operate satisfactorily and maintain structural integrity under all conditions that the aircraft may en- counter, including forces or conditions caused by acceleration, launching, de- ce

20、leration, arresting, zero gravity (g) , negative g, flight attitudes obtainable with the aircraft, structural deflection, vibration, or other environmental conditions. The bleed air system shall be so routed that a failure of any duct or component shall not result in the direct impingement of hot ai

21、r on any of the functional systems in the aircraft which would affect safety of flight. 3.4.7.1 Drainage provisions - Drainage provisions shall be incorporated in the system and its components to prevent the accumulation of rain or washing water. 3.4.8 Component design - The bleed air system may con

22、sist of the following components - compressor bleed air fittings, distribution ducts, auxiliary duct units, brackets, hinges, fittings, unions, clamps, gaskets, bellows, coupling assemblies, expansion joints, nozzles, spacers, insulation, heat shields, shut- off valves including linkages and drives,

23、 pressure and temperature gages, and check valves. 3.4.8.1 Selection of components - Any component included in the bleed air system shall have been tested to indicate suitability of design. These tests Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-

24、MIL-B-$1365 (W) shall be in accordance with the suppliers approved equipment specifications and shall include life and performance tests plus the following applicable environmental tests in accordance with MIL-E-5272, (a) High temperature, Procedure II (b) Low temperature, Procedure II (c) Humidity,

25、 Procedure I (d) Altitude, Procedure VI, Condition in accordance with operating altitude (e) Salt spray, Procedure II (f) Shock, Procedure V (g) Vibration, Procedure XIV (h) Sand and dust, Procedure I (i) Fungus resistance, Procedure I 3.4.8,2 Reverse installation - Components whose proper operation

26、 is subject to direction of flow shall be so designd that they cannot be installed rever sed. 3.4.8.3 Duct design - The ducting shall be constructed of corrosion resistant metal. 3.4.8.3.1 Duct wall thickness - Minimum wall thickness may be dicta- ted by damage occurring during fabrication or handli

27、ng. The following minimum wall thickness shall be adhered to. Duct diameter (inches) Min. wall thickness (inches) Under 1.00 o O10 .o. 012 O. 016 o. 020 O; 025 as required by design over 1.00 to 2.00 over 2.00 to 3.50 over 3.50 to 5.00 over 5.00 to 6.00 Over 6.00 5 K Provided by IHSNot for ResaleNo

28、reproduction or networking permitted without license from IHS-,-,-MIL-B-L3b5 Lb 7977906 0204550 M MIL-B- 81365 (W) 3.4.8.3.2 Standard sizes - The duct shall be designed and fabricated to the diameters shown below: Outside diameter(inches) Size increments (inches) 0.75 to 4.00 over 4,OO O. 25 0.50 3.

29、4.8.4 MS24563. procuring agency. Nuts used for couplings shall be of a torque limiting type, approved by the procuring activity. Couplings - Couplings shall conform to MIL-C-27536 and The selection of other types shall be subject to the approval of the 3.4.8.5 Expansion devices - Suitable devices to

30、 absorb deflection shall be installed in the duct installation as required, Supports shall be provided on each side of the device as close as practicable to the device. Only one support may be fixed, With the system operating at the most adverse combination of temperature, pressure, and airframe def

31、lections, there shall be no misalignment or deformation of these devices or components that will adversely affect the performance of the system. 3.4.8.6 Shut-off valve - Valves shall be provided to control the air flow of the bleed air system. The valves shall be incorporated as near as practicable

32、to the air source and shall be mounted by means that will prevent malfunction due to vibration. 3.4.8.7 Branch duct joints - Flat areas inherent in the design of Ys and Ts shall be kept to an absolute minimum. Areas that are normally flat shall be crowned as much as is practicable, The crotch area o

33、f tiYil sections shall be reinforced when subjected to adverse mechanical and thermal loads, 3.4.8.8 Brackets - Brackets which are assembled to ducts by welding shall not be welded directly to the duct walls, The bracket shall be welded to a doubler, and the doubler shall be welded to the duct wall.

34、 3.4.8.9 Screw threads - Screw threads shall conform to MIL-S-7742 or MIL-S-8879. 3.5 Performance - The bleed air system shall meet the following performance requirements and any additional requirements specified in the detail specification. Provided by IHSNot for ResaleNo reproduction or networking

35、 permitted without license from IHS-,-,-MIL-B-81365 16 m 7779706 020q551 T m -* MIL.-B-81365 (WP) 3.5.1 Proof pressure - The bleed air system components shall with- stand, at operating temperature, a pressure equal to twice the operating pressure without evidence of permanent deformation, malfunctio

36、n, or leakage. 3.5.2 Endurance - The bleed air system ducting shall withstand, at operating temperature, a minimum of 15,000 cycles between the operating pres- sure and a pressure within 10 percent of the specified minimum operating pres- sure with a duration of impulse not longer than O. 05 second

37、at a rate of pressure rise between 12,000 and 15,000 psi per second without evidence of leakage, per- manent deformation, or structural failure. 3.5.3 Vibration - The bleed air system bellows, valves, and ducting incorporating welded brackets for support shall withstand vibration in accordance with

38、the frequency - amplitude profile of vibration test Procedure XIV of MIL-E- 5272 without evidence of cracking, permanent deformation, or structural failure. 3.5.4 Flow resonance - The bleed air system flex sections shall withstand resonant or chattering conditions due to flow for a total of 100 hour

39、s at the operating pressure and temperature without evidence of leakage, permanent deformation, or structural failure. 3.5.5 Burst pressure - The bleed air system components shall with- stand, at operating temperature, a pressure equal to four times the operating pressure without evidence of leakage

40、 or rupture. Permanent deformation shall be permitted. 3.6 cable reflecting the existing stage of technological development and current in- dustrial practice. Weight - The weight of the system shall be as low as practi- 4. QUALITY ASSURANCE PROVISIONS 4.1 Responsibility for inspection - Unless other

41、wise specified in the contract or purchase order, the supplier is responsible for the performance of all inspection requirements as specified herein. Except as otherwise specified, the supplier may utilize his own facilities or any commercial laboratory acceptable to the Government. The Government r

42、eserves the right to perform any of the in- spections set forth in the specification where such inspections are deemed necessary to assure supplies and services coriform to prescribGd requirements. 4.2 Inspection methods - 4.2.1 Examination - The system shall be thoroughly examined to 7 Provided by

43、IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-B- 81365 (WP) determine conformance with this specification and applicable drawings with respect to all the requirements not covered by tests specified,herein. 4.2.2 Proof pressure - The equivalent prod pressur

44、e which will result in stresses equal to those applied by the combined pressure and temperature at operating conditions may be approximated by P Po = working pressure at operating temperature, poundF 31 square inch PT = proof pressure at test temperature, pounds per square inch = maximum allowable t

45、ensile yield stress value at the operating temperature, pounds per square inch = maximum allowable tensile yield stress value at the test temperature, pounds per square inch ST Each system component shall be tested with water at room temperature. After bleeding all air from the component and pluggin

46、g all outlets, a proof pressure (P ) shall be applied twice, at a rate not exceeding 25,000 psi per minute, and shall be held for a period of two minutes for each application. The pressure shall be reduced to zero between applications. Each component shall meet the proof pressure requirements specif

47、ied in 3.5.1. T 4.2.3 Endurance test - The ducting (including expansion devices and branch duct joints) shall be subjected to a pressure cycling test at room tempera- ture with the test pressure adjusted to compensate for the reduction in allowable sfxess that would occur at the operating temperatur

48、e (P E = Cl( 2) (see 4.3.2),). PE = endurance pressure at test temperature, pounds per square inch The ducting shall be cycled for 15,000 cycles between the adjusted test pressure (PE) and a pressure within 10 percent of the minimum operating pressure. The duration of impulse shall be no longer than

49、 O. 05 second and the rate of pressure rise shall be between 12,000 and 15,000 psi per second. The ducting shall meet the endurance requirements specified .in 3.5.2. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-0-81365 Lb M 7797706 0204553 3 - -. MIL-B- 81365 (WP) 4.2.4 Vibration - Bellows , valves, and ducting incorporating welded brackets for supp