SAE ARP 1755B-1993 Effect of Cleaning Agents on Aircraft Engine Materials Stock Loss Test Method《清洗剂对飞机发动机物料损失的影响的测试方法》.pdf

《SAE ARP 1755B-1993 Effect of Cleaning Agents on Aircraft Engine Materials Stock Loss Test Method《清洗剂对飞机发动机物料损失的影响的测试方法》.pdf》由会员分享，可在线阅读，更多相关《SAE ARP 1755B-1993 Effect of Cleaning Agents on Aircraft Engine Materials Stock Loss Test Method《清洗剂对飞机发动机物料损失的影响的测试方法》.pdf（23页珍藏版）》请在麦多课文档分享上搜索。

1、SAE 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 entirelyvoluntary, and its applicability and suitability for any particular use, including any patent infringement arising therefro

2、m, is the sole responsibility of the user.”SAE reviews each technical report at least every five years at which time it may be reaffirmed, revised, or cancelled. SAE invites your written comments and suggestions.Copyright 2000 Society of Automotive Engineers, Inc.All rights reserved. Printed in U.S.

3、A.TO PLACE A DOCUMENT ORDER: (724) 776-4970 FAX: (724) 776-0790SAE WEB ADDRESS: http:/www.sae.org400 Commonwealth Drive, Warrendale, PA 15096-0001AEROSPACE RECOMMENDED PRACTICEARP1755REV.BIssued 1984-01-01Revised 1993-01-01Reaffirmed 2000-03Superseding ARP1755AEffect of Cleaning Agents on Aircraft E

4、ngine MaterialsStock Loss Test Method1. SCOPE:1.1 This SAE Aerospace Recommended Practice (ARP) covers the determination of the amount of stock loss caused by use of chemical cleaning agents on aircraft turbine engine materials.1.2 The evaluation is conducted on representative engine materials by de

5、termination of weight loss during total immersion in the cleaning solution with the weight-loss measurement converted to stock loss by calculation.1.3 Test conditions are based upon manufacturers recommended operating parameters for maximum concentration, maximum temperature, and twice the maximum i

6、mmersion time.1.4 Chemical cleaning solutions and compounds used for preinspection cleaning of aircraft turbine engine parts shall be subject to requirements of this test practice.1.5 The test does not give consideration to cleaning performance of the compounds except as specified in 5.1.4.1.6 Class

7、ification:Examples of types of cleaning materials to be qualified under the requirements of this test procedure are:a. Category 1: Cold carbon and paint removerb. Category 2: Alkaline rust removerc. Category 3: Alkaline oxide conditionerd. Category 4: Acidic oxide conditionere. Category 5: Alkaline

8、permanganate oxide conditionerf. Category 6: Inhibited phosphoric acidg. Category 7: Hot carbon and paint removerh. Category 8: Silicone rubber removeri. Category 9: Antigalling compound removerSAE ARP1755 Revision B- 2 -1.6 (Continued):j. Category 10: Aqueous cleanerk. Category 11: Alkaline degreas

9、erl. Category 12: Organic solvent cleaner1.7 Safety - Hazardous Materials:While the materials, methods, applications, and processes described or referenced in this aerospace recommended practice may involve the use of hazardous materials, this aerospace recommended practice does not address the haza

10、rds which may be involved in such use. It is the sole responsibility of the user to ensure familiarity with the safe and proper use of any hazardous materials and to take necessary precautionary measures to ensure the health and safety of all personnel involved.1.8 Significance:This aerospace recomm

11、ended practice establishes a test procedure for determining the metal removal characteristics of aircraft turbine engine cleaning materials when used on a representative list of aircraft turbine engine alloys and coatings. This test result shall be compared with the following maximum stock loss per

12、surface to establish acceptability for overhaul shop evaluation of cleaning performance characteristics:a. Bare Panels or Disks: 0.000025 in (0.635 m)b. Electroplated Panels: 0.000025 in (0.635 m)c. Plasma Coated Panels or Bars: 0.000100 in (2.5 m)2. APPLICABLE DOCUMENTS:The following publications f

13、orm a part of this aerospace recommended practice to the extent specified herein. The latest issue of SAE publications shall apply.2.1 SAE Publications:Available from SAE, 400 Commonwealth Drive, Warrendale, PA 15096-0001.AMS 2400 Cadmium PlatingAMS 2406 Chromium Plating, Hard DepositAMS 2410 Silver

14、 Plating, Nickel Strike, High BakeAMS 2416 Nickel-Cadmium Plating, DiffusedAMS 2418 Copper PlatingAMS 2424 Nickel Plating, Low-Stressed DepositAMS 2437 Coating, Plasma Spray DepositionAMS 2470 Anodic Treatment of Aluminum Alloys, Chromic Acid ProcessAMS 3065 Compound, Corrosion Preventive, Thin Film

15、, Fingerprint RemovingAMS 4037 Aluminum Alloy Sheet and Plate, 4.4Cu-1.5Mg-0.60Mn (2024; -T3 Flat Sheet, -T351 Plate)SAE ARP1755 Revision B- 3 -2.1 (Continued):AMS 4375 Magnesium Alloy Sheet and Plate, 3.0Al-1.0Zn (AZ31B-O)AMS 4442 Magnesium Alloy Castings, 3.3Ce-2.5Zn-0.70Zr (EZ33A-T5)AMS 4507 Bras

16、s Sheet, Strip, and Plate, 70Cu-30Zn (CDA26000), Half HardAMS 4544 Alloy Sheet, Strip, and Plate, Corrosion Resistant, 67Ni-30Cu, AnnealedAMS 4640 Aluminum Bronze Bars, Rods, Forgings, and Tubing, 81.5Cu-10.3Al-5.0Ni-2.8FeAMS 4911 Titanium Alloy Sheet, Strip, and Plate, 6Al-4V, AnnealedAMS 4928 Tita

17、nium Alloy Bars, Forgings, and Rings, 6Al-4V, Annealed 120,000 psi (825 MPa) Yield StrengthAMS 5040 Steel Sheet and Strip, 0.15 max Carbon, Deep Forming GradeAMS 5382 Alloy Castings, Investment, Corrosion and Heat Resistant, 54Co-25.5Cr-10.5Ni-7.5WAMS 5504 Steel Sheet, Strip, and Plate, Corrosion an

18、d Moderate Heat Resistant, 12.5Cr (SAE 51410)AMS 5508 Steel Sheet, Strip, and Plate, Corrosion and Moderate Heat Resistant, 13Cr-2.0Ni-3.0WAMS 5524 Steel Sheet, Strip, and Plate, Corrosion and Heat Resistant,18Cr-13Ni-2.5Mo (SAE 30316)AMS 5525 Steel Sheet, Strip, and Plate, Corrosion and Heat Resist

19、ant, 15Cr-25.5Ni-1.2Mo-2.1Ti-0.006B-0.30VAMS 5536 Alloy Sheet, Strip, and Plate, Corrosion and Heat Resistant, 47.5Ni-22Cr-1.5Co-9.0Mo-0.60W-18.5FeAMS 5537 Alloy Sheet, Corrosion and Heat Resistant, 52Co-20Cr-10Ni-15WAMS 5544 Alloy Sheet, Strip, and Plate, Corrosion and Heat Resistant, 57Ni-19.5Cr-1

20、3.5Co-4.2Mo-3.0Ti-1.4Al-0.05Zr-0.006B, Consumable Electrode or Vacuum Induction Melted, AnnealedAMS 5596 Alloy Sheet, Strip, and Plate, Corrosion and Heat Resistant, 52.5Ni-19Cr-3.0Mo-5.1(Cb+Ta)-0.9Ti-0.5Al-18Fe, Consumable Electrode or Vacuum Induction Melted, 1750F (955C) Solution Heat TreatedAMS

21、5613 Steel Bars, Forgings, Tubing, and Rings, Corrosion and Moderate Heat Resistant, 12.5Cr (SAE 51410), AnnealedAMS 5661 Alloy Bars, Forgings, and Rings, Corrosion and Heat Resistant, 42.5Ni-12.5Cr-5.8Mo-2.9Ti-0.015B-35Fe, Consumable Electrode or Vacuum Induction Melted, Solution, Stabilization, an

22、d Precipitation Heat TreatedAMS 6431 Steel Bars, Forgings, and Tubing, 1.05Cr-0.55Ni-1.0Mo-0.11V (0.45-0.50C), Premium Quality, Consumable Electrode Vacuum Melted3. MATERIALS:Test materials shall conform to specification requirements or to composition requirements in Figure 1, as applicable. Test ma

23、terials shall be obtained from commercial sources as available. When a test material is not commercially available, it may be obtained from the applicable engine manufacturer as indicated under Test Materials Sources, Figure 1.SAE ARP1755 Revision B- 4 -4. SPECIMEN PREPARATION:4.1 Materials:Shall be

24、 as listed in Tables 2, 3, and 4.4.2 Preparation of Test Panels, Disks, and Electroplated Panels:Complete lists of test materials are given in Tables 2 and 3. Test material requirements for specific cleaning compound categories are given in Figure 1. Use Figure 1 to determine test material requireme

25、nts for a specific cleaning compound category.4.2.1 Prepare 2 x 5 in (51 x 127 mm) panels from sheet or strip or transverse cross-section disks with parallel ground faces cut from conveniently sized bars, and drill or punch a 1/8 in (3.2 mm) diameter hole near one end if needed for suspension.4.2.2

26、Deburr edges after cutting and drilling or punching.4.2.3 Wet abrasive blast test specimens all over, using approved alumina or silica abrasive or nonsilicone treated glass beads nominally 0.001 to 0.003 in (0.02 to 0.08 mm) in diameter. Machine air pressure to be 60 to 100 psi (414 to 689 kPa). Spe

27、cimens may be prepared using dry blasting methods with 500 mesh alumina. Air pressure requirements are 25 to 30 psi (172 to 207 kPa) on a direct pressure machine or 50 to 60 psi (345 to 414 kPa) using a suction type dry blasting machine.4.2.3.1 Examples of approved abrasive media are: Novaculite No.

28、 200 available from Wheelabrator-Frye, Inc., Mishawaka, IN 46544, or from Vapor Blast Manufacturing Co., Milwaukee, WI 53209, or UNI-SS (280 to 500 mesh) from Abrasive Developments, Henley-in-Arden, Solihull, Warwickshire, UK or equivalent materials.4.2.4 Number each individual panel or disk for per

29、manent identification.4.2.5 For electroplated panels, electroplating shall be in accordance with requirements of Table 3.4.3 Preparation of Plasma Coated Test Panels and Bars:A complete list of plasma spray materials is given in Table 4. Test material requirements for specific cleaning compound cate

30、gories are given in Figure 1. Use Figure 1 to determine test material requirements for a specific cleaning compound category.4.3.1 Preparation of Test Panels:4.3.1.1 Cut 1 x 3 in (25 x 76 mm) panels and drill or punch a 1/8 in (3.2 mm) diameter hole in each panel for suspension purposes.4.3.1.2 Debu

31、rr all edges.SAE ARP1755 Revision B- 5 -4.3.1.3 Grind one side of panel flat to approximately 30 in (0.08 m) finish.4.3.1.4 Plasma spray coat the ground side of the panel to a thickness of 0.010 to 0.012 in (0.25 to 0.30 mm).4.3.1.5 Grind coated side to leave 0.003 to 0.005 in (0.08 to 0.13 mm) of c

32、oating thickness.4.3.1.6 Remove overspray from edges of panel.4.3.1.7 Number panel and identify plasma coating type on the uncoated side of each individual panel for permanent identification.4.3.2 Preparation of Test Bars:4.3.2.1 Cut corrosion-resistant steel bar specimens 4.0 x 0.32 in (102 x 8.1 m

33、m).4.3.2.2 Deburr all edges.4.3.2.3 Grind the bar to approximately 30 in (0.08 m) finish.4.3.2.4 Degrease using any degreasing method approved by engine manufacturer or overhaul facility.4.3.2.5 Dry abrasive blast, excluding end faces, using 24/36 grade aluminum oxide grit. Air pressure requirements

34、 are 25 to 30 psi (172 to 207 kPa) on a direct pressure machine or 50 to 60 psi (345 to 414 kPa) using a suction type dry blasting machine. Clean with a dry air blast to remove residual grit.4.3.2.6 Apply plasma spray coating to a thickness of 0.010 to 0.012 in (0.25 to 0.30 mm).4.3.2.7 Grind the co

35、ating to leave 0.003 to 0.005 in (0.08 to 0.13 mm) of coating thickness.4.3.2.8 Remove overspray from edges of panel.4.3.2.9 Number bar on end face and identify plasma coating type on each bar for permanent identification.5. TEST PROCEDURES:5.1 General Instructions:Evaluation testing of aircraft tur

36、bine engine cleaning chemicals shall be accomplished as follows:5.1.1 Determine the category into which the cleaning chemical falls as shown in Table 1.5.1.2 Test the required panels, disks, or bars listed in Tables 2, 3, and 4 and Figure 1, using the prescribed number of serialized specimens for ea

37、ch test.SAE ARP1755 Revision B- 6 -5.1.3 Enter stock loss and related information on a stock loss data chart as in Figure 2 and forward with letter of transmittal to applicable engine manufacturer(s).5.1.4 If the results are within prescribed limits, the chemical cleaner shall receive preliminary ap

38、proval of its applicability and the engine manufacturer shall permit performance testing of the cleaner in an appropriate engine overhaul facility. After the cleaner has been in use with a recognized overhaul shop on turbojet and turbofan engines for not less than 6 months and has been used for clea

39、ning at least 10 engines or equivalent, with favorable experience, the cleaner shall be approved by the engine manufacturer for service use.5.1.5 Panels, disks, or bars representing stock loss data submitted to engine manufacturers on the stock loss data chart shall be serialized and retained by the

40、 cleaning compound manufacturer for not less than one year after completion of the cleaning compound approval procedure. The serial number of each specimen shall be recorded in the appropriate place on the form. A serialized specimen shall be used for one test only. Specimens retained by the vendor

41、shall be preserved as described in 5.4 to prevent any change in physical condition.5.1.6 Cleaning compound with revised formulation or operating parameters shall be retested to the requirements of the testing procedure and be reapproved by the engine manufacturer before the reformulated cleaning com

42、pound may be submitted to engine overhaul facilities for service testing.5.1.7 Do not submit samples of turbine cleaning materials to engine manufacturers or engine overhaul facilities unless specifically requested. Do not submit proprietary information relative to engine cleaning materials.5.2 Test

43、 Requirements:Testing of any cleaning material for turbine engine use shall be conducted in accordance with the following:5.2.1 Requirements are given in Tables 2, 3, and 4 and Figure 1. If the vendor feels that the test specimen material or coating is incompatible with the cleaning solution, N.R. (

44、Not Recommended) may be entered on the stock loss data chart of Figure 2.5.2.2 The strength of the chemical being tested shall be at the top limit of the vendors recommended operating limits; e.g., if 12 to 16 fluid ounces per gallon (95 to 125 ml/L) are recommended, use 16 fluid ounces per gallon (

45、125 ml/L) for testing.5.2.3 The temperature of the chemical being tested, if other than room temperature, shall be at the top limit of the vendors recommended operating limits; e.g., if a range of 190 to 210 F (88 to 99 C) is recommended, use 210 F (99 C) for test purposes.5.2.4 Exposure time for th

46、e test specimens shall be double the vendors recommended engine part processing time. If vendors instructions include a recommendation that the cleaning solution be agitated, the test shall be performed in vigorously agitated cleaning solution using the vendors recommended method of agitation.SAE AR

47、P1755 Revision B- 7 -5.2.5 If chemical strength and/or processing time differs for application to titanium parts, all details regarding this difference shall be indicated in the remarks space on the stock loss data chart of Figure 2 and stock loss figures based thereon entered on the chart for titan

48、ium.5.2.5.1 The requirements of 5.2 shall apply for any modified procedure.5.3 Stock Loss Test:5.3.1 Sheet Alloy Panels or Disks and Electroplated Panels (3 Each):5.3.1.1 Prepare specimens as in 4.2.5.3.1.2 Degrease using any degreasing method approved by engine manufacturer or overhaul facility.5.3

49、.1.3 Rinse in alcohol or acetone.5.3.1.4 Air dry for 15 to 20 min or oven dry at a temperature below 200 F (93 C) and air cool, and immediately weigh panel or disk to nearest milligram and record weight (Wi).5.3.1.5 Suspend test panel or disk not less than 2 in (51 mm) below the surface of the cleaning solution being tested for the time specified.5.3.1.5.1 In order to avoid possible error by galvanic action between the specimen and the tank or other grounding source, the specimen should be suspended without contact in the cleaning solution using a corr