NAVY MIL-P-81513-1967 POWER UNIT AIRCRAFT AUXILIARY GAS TURBINE TYPE I NAVY MODEL NO P-7《飞机辅助汽油涡轮 I类 海军P-7号模型能量单位》.pdf

《NAVY MIL-P-81513-1967 POWER UNIT AIRCRAFT AUXILIARY GAS TURBINE TYPE I NAVY MODEL NO P-7《飞机辅助汽油涡轮 I类 海军P-7号模型能量单位》.pdf》由会员分享，可在线阅读，更多相关《NAVY MIL-P-81513-1967 POWER UNIT AIRCRAFT AUXILIARY GAS TURBINE TYPE I NAVY MODEL NO P-7《飞机辅助汽油涡轮 I类 海军P-7号模型能量单位》.pdf（10页珍藏版）》请在麦多课文档分享上搜索。

1、13 January 1967 . - .: . . _ . i- .- . _- . . . . _-. : .- -. . . .: . :. . - . _- -. . .- .- lbdel Specification Power Unit; Aircraft Auxiliary Gas Turbine, Type I, Navy lbdel No. P-7 This specification has been approved by the Naval Air Systems Command, 1. ?!?%e. %is spec a fuel system including a

2、 unit driven fuel pump, fuel filter, fuel control for controlling speed and overspeed, and six vaporizing fuel nozzles. also provided which is cut-out at 9% unit speed. components include an ignition exciter (powered from the airframe instal- lation), a single spark ignitor, tachometer generator, ex

3、haust gas tempera- ture themcouple, thermal switch, start counter, overspeed switch and speed switch. The gas turbine auxiliary power unit (APU) as defined The APU consists of The accessory gearbox also provides support for the lubri- The unit A starting fuel nozzle is The electrical system 2. Appli

4、cable bcuments. 2.1 Auplicabililx. The following specifications, standards, drawings, and publications, of the issue specified below, shall form a part of this speci- fication only to the extent specified herein or in the referenced paragraphs of Spec Ffica tiaWp-8 68 6: THIS DOCUMENT CONTAINS 10 PA

5、GES. I. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-P-81513 (AS) Fedaral TTS-735 Standard Test Fluids; Hydrocarbon. I .- . _ _. . EimuKz MIL-C-3702 MILE-5007 MIL-J-5161 MIL-E-5607? MIL- J-5 624 MIL-1-6181? MILF-7024 MILS-7742 KILL-7808 1p-868

6、6 MIGS-8879 Cable, Power, Electrical; Ignition, High-Tension. mgines, Aircraft, Turbo jet; General Specification for. Jet Fuel, Referee. Ehgine, Gas Turbine, Preparation for Storage Jet Fuel, Grades JP-4 and JP-5. Interference Control Requirements, Aircraft Fluid; Calibrating, for Aircraft Fuel Syst

7、em Screw Threads, Standard, Optimum Selected Series: Lubricating Oil, Aircraft Turbine ihgine, Power Units; Aircraft Auxiliary, Gas Turbine Screw Threads, Controlled Radius Root with and Shipment, Process for. Equipmen t. Components. General Specification for. Synthetic Engineering and Associated Li

8、sts. Container, Shipping, Metal, Reusable 5 Cubic ihamel Equipment, Light Grey (Fornula 111). Lubricating Oil, Aircraft Turboproh?and Turbo- shaft mgines, Synthetic Base. Industry SDecifications dMSa-0 AMs2445 As478 Magnetic Particle Inspection. Fluorescent Penetrant Inspection. Identification Marki

9、ng Methods. Military Standards MIL-STD.130 Identification Marking of US Military Property. - - MILSTD-210 Climatic Extremes for-Miitary Equipment. =SIL453 inspection, Radiographic IS33540 Safety Wiring, General bactices for. M33586 Metals, Definition of Mssimilar. 2 Provided by IHSNot for ResaleNo r

10、eproduction or networking permitted without license from IHS-,-,-._ -. . .I .- . . , . - . .-. E433666 E33668 AN10050 AND20002 AND20005 Packing, Preformed - Aeronautical, Elstomeric, Packing, Reformed - Pipe Fitting, Elastomeric, Bosses, Sksndard Mmensions for Gasket Seal Drive-Type 1114 Ehgine Acce

11、ssory. Drive-Type XV-B EhgFrre Accessory. Range of Sizes. Range of sizes. Straight Thread. I Mr Force-Naw Aeronautical ailletins AN11182r ANA343 ANA423 mu38 ANUS Material Changes and Substitutions; Aircraft Specifications and Standards Applicable to fhgines; Mrcraft, Vendor Substantiation Tests for.

12、 Age Controls of Age-sensitive ELastomeric Items. hginering Changes to Weapons, Systems, Equip- mgFne Parts. Aircraft 4-19L9. 2.2 suo ersedencq. If any of the documents forming a part of this speci- fication are superseded by a later document, revision, or amendment, it shall be permissible ta apply

13、 such later documents or supersding issues, insofar as such superseding requirements are equivalent ta or exceed the requirsments of this specification or of the docum+nta forming a put hereof as may be app-roved by the Government. . 3.0 ReauireLnenta. 3.1.1 Critical . gaskets used in the design of

14、the unit shall conform to the applicable dimensions and tolerances shown on MS33666 and MS33668. ring seals shall not be marked with any identification. All nonmetallic IfOtt ring seals and 3.1.3.4 Ane Controls. with the requirements of ANA Bulletin No. 438. Age controls for synthetic rubber parts s

15、hall comply 3.1.4 Material. Processes and Products. Materials, processes and products used in the manufacture of aiuciliary power units shall be of high and con- sistent quality, shall be suitable for the purpose, and shall conform to the applicable specifications selected in accordance with ANA Bul

16、letin No. 343. Where contractors specifications are used for materials and processes, such specifications shall be submitted to the Government for review prior to preproduction test, and unless specifically disapproved will be considered released upon satisfactory completion and approval of the unit

17、 preproduction tests. waiver of Govenunent inspection. Approval of non-Government specifications shall not constitute 3.1.4.1 Standard Parts. are positively determined to be unsuitable for the purpose, and shall be identified by their standard part numbers. in particular, standard parts released by

18、AN Wetin No. 343 are preferred and willibe considered for use prior to consideration of any other standLnd. Where general purpose standards, as identified by envelope dimensions or Qualified Products Lists (QPLs), are used in critical or high strength applications, they shall be identified by the ve

19、ndor or contractors part number. Parts derived from general purpose standards solely on an inspection or selection basis, shall be identified by the contractors part numbers (not necessarily on the part), and ail previous identification marks shall be removed. 3.2.1 Standardization. Standardization

20、principles shall be applied at all phases of initial design and ia all design changes. Since these principles have, as final objectives, the reduction of varieties of unit components (e.g., materials, sizes, design elements, need for special tools, etc.,) both within a particular rmdel, and between

21、various models supplied to the military serqices, parts (restricted to the minimum number of varieties within that series) vill assure that such standardization is accomplished. are determined to be unsuitable for use in a specific application, the variety of special parts used shall be restricted i

22、a the most practicable limit. Under conditions wherein economics of production conflict with shdardization objectives, the latter group will govern or the using service shall be requested to select the component desired for use. AN or MS standard parts shall be used unless they . use of military and

23、 recognized industry standard When standard parts 4 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-P-81513 (AS) .- -* - -e . .I 3.3 Mdel SDecucation. This specification conforma to the del specification requirements specified in MIL-P-8686. all

24、performance data contained in this specification are guaranteed values. _- _- - .- _. 0 -. Unless otherwise positively identified, _- - . - . - *_ . - -. -. :_-. , L i. I- 3.4 slg4uuati on and AcceDtanc e. predicated upon (i) the satisfactory completion and approval of a preproduction test conducted

25、 on a rototype unit in accordance with Appendix I of this specification and (2 P the satisfactory completion and approval of acceptance tests conducted on each production unit in accordance with Appendix II of this specification. The parts list of each production unit shall be as established by the

26、approved preproduction test except as specifically approved by the Government through the medium of engineering changes. The final acceptance of any unit ahall be 3.5 Performanc e Ciiaract eristics. specified herein. fuel in accordance with Specification MILJ-5161, Grade II, and oil in accordance wi

27、th Specification MIL-L-7808 or MIL-L-23699. shall be determined under he sole control of the automatic control system The performance characteristics shall be as These performance characteristics shall be determined using These performance characteristics . furnished on the unit. 3.5.1 Fuel TyDes. T

28、he unit shall function satisfactorily throughout its operat- ing range with fuel conforming to Specification MILJ-5624, grades JP-4 and JP-5. External control adjustments will be allowed to meet this requirement only for changing from one fuel type to another. specified herein will not be exceeded w

29、hen fuels having any of the variations in characteristics permitted by Specification MIL-J-5624, grades JP-4 and JP-5, are used. The unit internal fuel system shall incorporate controls necessary for operation of the unit at the altitude limits and ambient operating tempera- tures specified in 3.5.7

30、. Fuel pressure supplied at the unit fuel connection shall be from a minimum of 5 psi above the true vapor pressure of the fuel up to a maximum of 40 psi gage. In particular, the operating limits * Fuel Twes Fuel Inlet Temeratures for Startinn and ODer atu JP-4 Jp-5 Minimum Maxirmim -6 50F 13 50F -L

31、OOP 135OF - _- -. “Provided the fuel viscosity is not more than 12 centistokes. . .- - .- .- 3.5.2 Puel Con tamination. fuel contaminated to the extent specified in Specification MILE5007 except the concentration of cotton linters shall be 0.1 gm/1ooO gal. The unit shall function satisfactorily when

32、 using ;.- A fuel filter shall be provided and shall be capable of 10 hours of continuou operation at the maximum rating shown in Table I, with the type of contaminant specified above added to the fuel. the interval between filter cleanings shall be a mininaun of 200 hours. For operation with nod fi

33、el, 5 _. 7-14. - ._ _. . . . . ._ : . -. - . . . . . . -. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-P-81513 (AS) 3.5.3 -. KIL-L-7808 or MIL-L-23699 used as the lubricant,throughout the nmbient altitude and temperature ranges specified herei

34、n for operating conditions. (See 3.5.7) 3.5.4 m. when using fuel conforming to Specification MILJ-5161, grades I and II, and oil conforming to Specification MIL-L-7808 or MIL-L-23699. based on no restriction at the unit air inlet or exhaust, and no loading of the accessory drives. The unit shal be c

35、apable of satisfactory operation, with The performance ratings of the unit are as listed in Table I These data are Table I Performance Ratings (U.S. Standard Sea Level Pressure and Temperature and with no air inlet or exhaust. losses) *Total Fuel Axial Side Rated BHP Output Consum tion Shaft Shaft M

36、easured (lbphr) Speed Speed ECT - - . - (WM) (RPM1 (OF) . -. _ . _. ,- . * * . = .- - . Min Nominal Nominal Nominal Nominal . .-. - . . - . . I . . . . . . -._ Maxirmnn 75 92 7790 7585 990 Normal 65 87 7840 7635 910 75% Normal 48.7 76 7920 7712 800 50% Normal 32.5 66 8000 7790 710 O O 47 8160 7945 5

37、80 *The combined maximum output from both pad drives is limited to 75 BHP. 75 BHP can be delivered from the axial drive pad alone. the side drive pad is limited to a .total of 65 BHP. *See 3.19 for steady state speed variation with load. However, Dueto gear design, NOTE: The above performance rating

38、s are based on the fuel louer heating value of 18,400 BTU/lb. 3.5.5 Estima tea. through 3 inclusive, and shall constitute a part of this specification. curves indicate the changes of the ratings of Table I with changes in ambient temperatures and pressureqand are based on other operating conditions

39、as specified in 3.5.4. The estimated performance curves are shown in Figures 1 These 3.5.5.1 Estimated Performanc e Curves. Figure 1. Shaft horsepower vs compressor total inlet temperature. FWG. hiel flow vs compressor total inlet temperature. 6 . r -. .I . . . Provided by IHSNot for ResaleNo reprod

40、uction or networking permitted without license from IHS-,-,-MTL-P-81513 (AS) . . .-. . .- -. -. -. . . -. - - . . ._ - : . is Figure 3. Operating speed tolerance. 3.5.5.2 Correction Datq. Figure 4. Figure 5. Altitude correction factor vs ambient temperature. Data for correction of performance for du

41、ct losses. 3.5.6 Oil Conswmtion. hour under any operating condition as specified herein. The oil consumption ehall not exceed 0.1 pound per 3.5.7 Altitude - Temperature Limits for Startine and ODeratirg. (1) Altitude Limita - The unit shall be capable of starting and operating satisfactorily from se

42、a level up to a pressure altitude of 6,000 feet when operating within the flight attitude conditions specified in 3.5.8. (2) TeInDerature Limitg - The maximum allowable ambient starting and operating temperatures for ground operatioli shall be 130F when supplied with fuel at a maximum temperature of

43、 135F, inlet air at a maximum temperature of l3WF and using the lubricants specified in 3.5. starting and operating temperature for inflight operation of the unit shall be within the hot atmosphere limits of MIL-STD-210. The minimum allowable ambient starting and o erating temperature for either gro

44、und or inflight opera- tion shall be minus 65 F when using MIL-L-7808 oil and Jp-4 fuel and minus 4OOF when using MIL-L-23699 oil and Jp-5 fuel. The maximum allowable ambient 8 satisfactorily under any of (i) Plus or minus (2) Plus or minus . . 3.5.8 Attitude Conditiong. * 3.5.8.1 Ground heratina At

45、titude. The unit may be installed and will operate the following conditions: 10 degrees displacement of the fore and aft axis. 10 degrees inclination to either side. . *. _. (3) Any combination of (i) and (2) above. 3.5.8.2 Fliaht heratine Attitude. satisfactorily with the gravity vector tilted 25 d

46、egrees in any direction from. the vertical axis passing through the center of gravity of the installed unit and shall be capable of operating satisfactorily without pramatuse ahutdoun or any other adverse effect on the unit under conditions of either negativa or zero *gn for up tk 10 seconds at a th

47、e. The unit shall be capable of operating 3.5.9 Ambient Temera ture Conditions. The complete unit vil1 perfom satisfactorily from sea level to 6,000 feet altitude at outputs from no load to nu 3.5.13.4 SDecial Startinn Fuel. Not Applicable. .- . ?. 3.5.13.5 Restart Time. In the event of a false star

48、t, the unit shall be - maintained inoperative for a 10 second period to allow the combustion chamber to be drained of residual fiel before another start sequence is initiated. 3.5.3-4 &g&num Rotor SDeed. of actuation of the overspeed switch shall not exceed 62,365 rp. governed unit rotor speed is 56

49、,695 rpm. axial output drive shaft speed is 7.09 to 1. 3.5.15 Section Protection. Not Applicable. I The maximum allowable rotor speed at the point The nod The ratio of rotor speed to the _. .- + -. - . - . . - . .- - . :- .: . . - . I ._ . - . - .-: .-.-: - -_ - - .- . - . . I i .- .- . - . . 3.6 Drawinns and Data. part of this specification: The following Solar Aircraft Company drawings form .a : 28677-0 Unit Basic Assem