1、 MIL-P-853LS 27 977770b OLIb3b7L 5 General Specification For Fuel System Components; General Specification For Anodic Coatiegs, for Aluminum and Aluminum Alloys Gcrew Threads, Controlled Radius Root with Increased Minor Diameter; General Specification for Plate, Tags and Bands for Identification of
2、 Equipment Aluminum-Alloy Castings, High Strength Nuts, Self-Locking 250F, 450F, 800F, 125 KSI FTU, 60 KSI FTU, and 30 KSI FTU Rubber, Fluorosilicone Elastomer, Oil and Fuel Recis tant Fluid, Calibrating, High Flash Point Aircraft Fuel Systems Components Turbiae Fuel, Aviation, Kerosene Type, Grade
3、Jl?-8 Rubber, Fluorocarbon Elastomer, High Temperature Metal, Test Methods Marking for Shipment: and Storage Identification Marking of US Military Property Specification and Standards Order of Precedence for Selection of Dissimilar etals Age Controls of Age-Sensitive Elastomeric Material. Wire, Safe
4、ty or Lock Packing Preformed Hydrocarbon Fuel Resistant O-ring Packing Pre-Formed Hydrocarbon Fuel Resistant O-ring Nuts and Plate Nuts, Self-Locking, ACFT Design also include a brief description of the ejector and its operation.) 2.0 APPLICABLE DOCUMENTS 2.1 The following documents, .of the issue i
5、n effect on date of invitation for proposals, form a part of this specification to the extent specified herein: SPECIFICATIONS Mil i ta ry MIL-P-85315 Pump, Ejector, Air Vehicle, Fuel, General Specification for MIL-G-5572 Gasoline, Aviation; Grades 80/87, 91/96, 100/130, 115/145 MIL-T-5624 Jet Fuel,
6、 Grades JP-3, JP-4, and JP-5 MIL-T-83133 Jet Fuel, Grade JP-8 STANDARDS Military (list all additional Government publications not covered this specification which are applicable to this pump). 3.0 REQUIREMENTS 3.8.1 Calibration - The ejector shall have the capacities, rated flows, dis- charge pressu
7、res, specified by the Contractor, using fuel in accordance with MIL-P-85315. (Insert the applicable specification number) 3.11 Dimensions - A drawing shall be furnished with this model specification, showing the outline and mounting dimensions for the ejector. 3.12 Mass - The weight of the ejector,
8、complete as a working assembly, shall not exceed kg 4,O QUALITY ASSURANCE PROVISIONS 4.6.2 Calibration - The ejector shall be operated over its entire permissible range of flow rates. (Data covering ,discharge pressure shall be recorded.) 16 Provided by IHSNot for ResaleNo reproduction or networking
9、 permitted without license from IHS-,-,-VIL-P-5315 27 9 7777906 01163707 5 = r- MIL-P-85315 4.6.3 Pressure Loss - With the motive flow zero (nozzle port blocked), fuel shall be drawn through the idle ejector by auxiliary means at flow from O to rated flow in kilograms per second. 4.6.4 Pump Down - T
10、he pump down level shall be no more than meters above the suction inlet. 4.6.5 Altitude - The ejector shall conform to the altitude climb curves as specified by the airframe manufacturer for the aircraft requirements and shall be within the minimum requirements of the altitude climb curves as shown
11、in Figure 5. All altitude climb tests shall be conducted with fuels conforming either to MIL-G-5572 or MIL-T-5624, as applicable. 4.6.8 Vibration tion testing). 5.0 PREPARATION - (The Contractor shall specify the procedures used in vibra- FOR DELIVERY 5.1 The preparation for delivery shall be in acc
12、ordance with (this specifica- tion no.) I 6.0 NOTES 6.1 ed application of the ejector in the aircraft). Intended Use - (The Contractor shall give a brief description of the intend- 17 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-10 .O8 II Iz O - t
13、 CT W v) v) W E 5 .O6 a .O4 e o2 O MIL-P-853L5 27 7777706 04b3708 7 MIL-P-85315 *EFFICI ENCY = fl EFFICIENCY* VS. - OPERATING LIMIT I I 1 I 1 i 3 4 5 FLOW RATIO = Ws/Wn .20 .16 .12 .O8 .O4 - N I O X - v - o Z LLI Figure 1. Typical Sea Level Performance Curve For Ejector Transfer Pump 18 Provided by
14、 IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-P-853L5 27 777970b 0463707 7 m MIL-P-85315 II IZ .2 O - UPPER OPERATING LIMIT /- OPERATING RANGE 1 OPERATING LIMIT O 1 1 I I I 2 3 4 5 O 1 FLOW RATIO 43 = Ws/Wn Figure 2. Typical Performance Curve for Ejector
15、Boost Pump With Negstive “G“ Capabilty 19 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-_I - _ I-_ MIL-P-5315 27 9 7977706 04b371O 5 W MIL-P-85315 fl vs. ALTITUDE * TIME vc. ALTITUDE I I l I t SL 3 6 9 12 15 SI 1 O00 750 v) 0 Z O w 500 v) 250 O TAN
16、K ALTITUTDE, METERS x lo3 Figure 3. Typical Altitude Performance Curve 20 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-P-85315 23 = 77737Ob 04b3711 7 U 5 ! U a MIL-P-85315 I .- a Il II II It a IR a IO n U O Un aci LI m IIIIIIIII IIIIIIIII IIII
17、IIIII c LOU+ 0a.A om 3 3 3 pi & &l&I&lP, 21 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-_ , MIL-P-85315 i9 W 999990b OLib3712 9 m 4 -9 MIL-P-85315 -4 TO RECORDER PRES SURE TRANSDUCER VACUUM PUMP TO RECORDER DIFFERENTIAL PRESSURE TRANSDUCER RE COR
18、DER To I PRES SURE TRANSDUCER r PRESSURE TRANSDUCER * PUMP /- I h -i=- .4 + - -c -. t t - XI_) _. FJ 1- EJECTOR FLOW TRANSDUCER TO RECORDER FLOW CONTROL TANK FLOW TRANSDUCER TO RE CORDER DIFFERENTIAL PRESSURE TRANSDUCER TO RECORDER * If needed to achieve desired dlscharge flowrate. * Figure 5. Typical Test Setup Schematic * If needed to achieve desired discharge flowrate. 22 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-
