1、 ACCEPTANCE CRITERIA FOR AMSC N/A FSC 2835 DISTRIBUTION STATEMENT A. Approved for public release; distribution is unlimited. THIS DOCUMENT ,CONTAINS -fl PAGES. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-STD-L8b7 28 W 7777733 0032347 8 = MIL-
2、 STD- 1 8 6 9 ( AT 1 .I I I I DEPARTMENT OF DEFENSE WASHINGTON, DC 20301 Turbine Blades and Vanes, Cast; Acceptance Criteria for 1. This Military Standard is approved for use within the US Army Tank-Automotive Command, Department of the Army, and is available for use by all Departments and Agencies
3、of the Department of Defense. - 2. Beneficial comments (recommendations, additions, deletions) and any pertinent data which may be of use in improving this document should be addressed to: AMSTA-GDS, Warren, MI 48397-5000, by using the self-addressed Standardization Document Improvement Proposal (DD
4、 Form 1426) appearing at the end .of this document, or by letter. US Army Tank-Automotive Command, ATTN: ii a a Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-STD-1869 28 W 7777711 0032LLI T W MIL-STD- 1869 (AT) FOREWORD This standard provides a
5、 means of insuring high-quality turbine blades and vanes iii Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. NOTICE OP 1 CHANGE 1 ab L I MIL-STD-l869(AT) N0tic.a 1 13 May 1991 MILITARY STANDARD TURBINE BLADES AND VANES, CAST; ACCEPTANCE CRITERIA FO
6、R TO ALL HOLDERS OF MIL-STD-l869(AT): 1. THE PAGES LISTED. THE FOUOWING PAGES OF MIL-STD-l869(AT), HAVE BEEN REVISED AND SUPERSEDE NIKmGE 9 10 11 12 17 li3 19 20 RATE 13 May 1991 23 November 1987 13 May 1991 13 May 1991 23 November 1987 13 May 1991 23 November 1987 13 May 1991 - 9 10 li 12 17 18 19
7、20 128TE 23 November 1937 Reprinted without change 23 November 1987 23 November 1987 Reprinted without change 23 November 1967 Reprinted without change 23 November 1987 2. 3, indicated above have been entered. check sheet. This issuance, together with appended pages, is a separate publication. Each
8、notice is to be retained be stocking Pqints until the military standard is completely revised or canceled. RETAIN THIS NOTICE AND INSERT BEFORE TABLE OF CONTENTS. Holders of MIL-STD-l869(AT) will verify that page changes and additions This notice page will be retained as a AMSC N/A PSG 2835 j. Appro
9、ved for public release; distribution is unlmited. 1 of 2 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-STD-3869 NOTICE 3 28 W 9999933 00999bb 5 = rc -: -3 4. mm . The margins of this standard are marked with vertical lines to indicate where cha
10、nges from the previous issue were made- liability whatsoever for any inaccuracies in these notations. Bidders and contractors are cautioned to evaluate the requirements of this document based on the entire content irrespective of the marginal notations and relationship to the last previous issue. Th
11、is was done as a convenience only and the Government assumes no Custarlian: Amy - AT Preparing activity: Amy - AT (Project 2835-AO25) 2 of 2 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-_I_ MIL-STD-LbS 28 SSSSSLL 00321LiS L e Paragraph 1 . 1.1 1.2
12、 1.3 2 . 2.1 2.2 2.3 3 . 3.1 3.2 3.2.2 3.2.3 3.2.4 3.2.5 3.2.1 4 . 5 . 5.1 5.1.1 5.1.1.1 5.1.1.2 5.1.1.3 5.1-1m3. 1 5.1.1.3.2 5.1.1.3.3 5.1mle3.4 5.1.1.3.4.1 5.1.1.3m4e2 5.1.1.3.5 5.1 -1 -3.6 5.1.2.2 5.1.2.3 MIL-STD-1869 (AT ) CONTENTS PAGE . REFERENCED IX)C.NTS . Issues of documents . Other publica
13、tions Order of precedence . DETAILED REQUIREMESmmmmmmmmeeeemmmomoommmmmmmmm Acceptance criteria . Type I Limits for imperfections (visual and fluorescent penetrant) . Surface coating . Burnish marks . Unacceptable defects Indentation and surface irregularities Acceptable defects Airfoil tip and plat
14、form Airfoil leading and trailing edge . Machined cooling holes and plug core positioning holes . Type II . Limits for imperfections (visual and fluorescent penetrant) . Indications of imperfections (radiographic) . Grain size Indications of imperfections (radiographic) . Root area masking and coati
15、ng limits 1 1 1 1 2 2 2 2 3 3 3 3 3 3 3 3 4 5 5 5 5 5 5 5 6 6 6 6 6 6 7 7 7 7 8 iv Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-i MIL-STD-3b7 28 W 777773L 0032350 I I* ! 5.1.3 5.1.3.1 5.1.3.2 5.1.3.3 5.1.3.4 5.1.3.4.1 5.1.3.4.2 5.1.3.4.3 5.2 5.2.1
16、 5.2.2 5.3 6. 6.1 6.3 6.2 Figure 1. 2. 3. 4. 5. 6. 7. Table I. II . III. MIL- STD- 1 8 6 9 ( AT) CONTENTS - Continued PAGE - Type III 8 Limits for imperfections (visual and fluorescent penetrant 8 Indications of imperfections (radiographic). 8 Grain size 9 Surface coating.m. 9 Burnish marks 9 Unacce
17、ptable defectsi. 9 Airfoil leading and trailing edge. 9 Identification marking 9 Types I and II 9 Type III 10 rework. 10 FIGURES Typical casting areas (type I). 13 Typical casting areas (type I) (continued). 14 Typical casting areas (type I). 15 Typical casting areas (type I). 16 Coating defects (ty
18、pe I). 17 Typical casting areas (type II) 19 Typical casting areas (type III). 21 Typical coating acceptance limits (typt? III). 22 TABLES Visual and fluorescent penetrant Visual and fluorescent penetrant Visual and flourescent penetrant acceptance limits (type I). 12 acceptance limits (type II) 18
19、acceptance limits (type III). 20 V Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I t i i i I I i 1 L I i i l I i l F I b 6 r i i 1 ! MIL-STD-1867 28 = 7777733 0032353 T - MIL- STD- 186 9 (AT ) 1. SCOPE 1.1 Scope. This standard covers the acceptance
20、 criteria for cast and finish-machined turbine blades and vanes, and blades assembled into wheels. 1.2 Purpose. The purpose of this standard is to insure turbine blades and vanes meet prescribed material acceptance criteria. 1.3 Classification. Classification shall be as follows: Type 1 Type II Type
21、 III - Air-cooled turbine blades. - Solid turbine blades. - Turbine vanes. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-STD-Lb7 28 = 77777LL 0032352 L I- MIL- STD- 1869 (AT ) 2. REFERENCED DOCUMENTS 2,l Issues of documents. The following docum
22、ents of the issue in effect on date of invitation for bids or request for proposal, form a part of this standard to the extent specified herein. STANDARDS MILITARY MIL-STD-453 MIL- STD- 1870 MIL-STD-6866 - Inspection, Radiographic. - Grain Size, Cast Turbine Blades, Acceptance - Inspection, Liquid P
23、enetrant Criteria for. (Copies of standards required by contractors in connection with specific acquisition functions should be obtained from the conCracting activity or as directed by the contracting officer.) 2.2 Other publications. The following document forms a part of this standard to the exten
24、t specified herein. Unless otherwise specified, the issue of the document which is DOI) adopted shall be that listed in the issue of the DODISS specified in the solicitation. The issue of the document which has not been adopted shall be that in effect on the date of the cited DODISS. SOCIETY AS OF A
25、UTOMOTIVE 478 ENGINEERS, INC. (SD) - Identification Marking Methods. (Application for copies should be addressed to the Society of Automotive Engineers, Inc., 400 Commonwealth Avenue, Warrendale, PA 15096.) (Nongovernment standards and other publications are normally available from the organizations
26、 which prepare or which distribute the documents. These documents also may be available in or through libraries or other informational services . ) 2.3 Order of precedence. In the event of a conflict between the text of this standard and the references cited herein, the text of this standard shall t
27、ake precedence. O: 1 J 2 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-STD-1869 ( AT 3 . DEFINITIONS 3.1 Casting lot. A casting lot is a group of castings with the same part number and revision letter, poured from one master heat of metal and u
28、sing the same casting process parameters and type of preheat and casting furnace . 3.2 Coatine turbine blade or vane. A coating is a material bonded to.the base metal of the t 3.2.1 Chip. A chip is an area of the coating which has been removed by a portion of the coating being flaked off. coating ed
29、ges. Chipping occurs most often along - 3.2.2 Spall. A spa11 is an area of the coating which has come off the coated area due to lack of bond to the base metal. 3.2.3 Blister. A blister is an area of coating raised above the plane of the coating due to lack of bond to the base metal. 3.2.4 Burnish.
30、A burnish is an area of the coating which has a luster or polish. 3.2.5 Crazing. Crazing is an area of the coating in which the formation of minute cracks occurs, usually attributed to shrinkage or sometimes $0 moist ur e . 3 Provided by IHSNot for ResaleNo reproduction or networking permitted witho
31、ut license from IHS-,-,-MIL-STD-LB67 28 W 77777LL 0032154 5 H MIL-STD- 1869 (AT ) 4. GENERAL REQUIREMENTS (Not applicable) I I 1 I 1 1 I I I I 4 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-STD-3869 28 7377333 0032355 7 m MIL-STD- 1869 (AT 5 D
32、ETAILED REQUIREMENTS 5.1 Acceptance criteria. 5.1.1 Type I. 5.1.1.1 Limits for imperfections (visual and fluorescent penetrant). Limits for imperfections for acceptance of turbine blade castings, determined visually and with fluorescent penetrant in accordance with MIL-STD-6866, shall be as follows:
33、 a. No evidence of cracks, dross, cold shuts, hot tears, linear or b. Unratable imperfections, pits, blowholes, bottomed porosity, crack-like indications, or linear inclusions. indications, etc. shall be within the allowable limits specified in table I. C. There shall be no evidence of positive meta
34、l on airfoil surfaces to be coated. d. The limits of table I may be exceeded on the as-cast surfaces provided the allowable limits of table I can be met after machining. e. Mold ridges, fins, and gate witnesses shall not exceed 0.030 inch in height. On the airfoil surfaces, mold ridges, fins, and ga
35、te witnesses shall not be permitted. 5.1.1.2 Indications of imperfections (radiographic). Indications of imperfections in turbine blade castings, determined by radiography in accordance with MIL-STD-453, shall be acceptable in the specified area (see table I and figures 1 and 3) provided identifiabl
36、eindications do not exceed the following limits: a. Casting area A. Identifiable indications in casting area A b. Casting areas B and C; shall not be acceptable. (i) Cracks, abnormal segregation, cold shuts, misruns, and hot tears shall not be acceptable. (2) Porosity, inclusions, positive metal, an
37、d shrinkage shall be acceptable provided the indications do not exceed 0.020 inch dimension or number more than four indications per blade casting and are not less than 0.25 inch apart. 5.1.1.3 Surface coating. Surface coating areas-of turbine blades shall meet the acceptance criteria of the applica
38、ble turbine blade drawing and the exceptions specified herein. 5.1.1.3.1 Burnish marks. Burnish marks (see 3.2.4) shall be permitted on the coating of turbine blades provided the coating is not removed below the allowable drawing thickness specified. 5 Provided by IHSNot for ResaleNo reproduction or
39、 networking permitted without license from IHS-,-,-MIL-STD-1869 28 = 799971i3 0032356 9 5.1.1.3.2 Unacceptable defects. There shall.be no evidence of defects on turbine blade airfoil and platform such as chips, spalls, blisters, and crazing (see 3.2) of the coating beyond the shaded areas illustrate
40、d in figure 4. 5.1.1.3.3 1ndentation.and surface irregularities. Indentation and surface irregularities on turbine blade castings which meet applicable drawing dimensional requirements shall be acceptable provided the coating is entire throughout the indented and irregular areas. 5.1.1.3.4 Acceptabl
41、e defects. 5.1.1.3.4.1 Airfoil tip and platform. Defects shall be allowed on the blade airfoil for a distance of 0.13 inch below the blade tip and on the blade platform (excluding the platform airfoil fillet radiusj as noted in figure 4. The following limits apply: a. Defects over 0.06 inch dimensio
42、n shall not be acceptable. b. Defects 0.03 to 0.06 inch dimension shall be acceptable provided there are not more than two per blade side. C. Defects under 0.03 inch dimension shall be acceptable provided there are not more than a combined total of six defects of any size on any one blade per side.
43、The distance of closest approach shall be not less than the maximum dimension of the smaller acceptable defect. d. 5.1.1.3.4.2 Airfoil leading and trailing edge. a. 0.030 inch maximum dimension. be C. 0.25 inch distance of closest approach to another indication. All indications must originate at, or
44、 cross over the leading or trailing edge radius. 5.1.1,3.5 Root area masking and coating limits. Coating applied to turbine blade root areas after machining is completed shall meet the limits specified on the applicable turbine blade drawing and the following requirements after masking material is r
45、emoved: a. Rejectable masking and coating material indications: (1) Masking or coating material exceeds 0.031 inch dimension. (2) (3) (4) The remaining material (masking or coating) forms a fillet More than five areas containing masking or coating material found in any one root area. The distance of
46、 closest approach between areas is less than 0.125 inch. .over 0.010 inch in the machined grooves. I I I I I I 1 I I 1 1 I 1 I 1 6 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-E i I MIL-STD-1869 28 9777713 0032157 O m b. Acceptable masking and coa
47、ting material areas: (1) Bottom of blade root: Areas of any size which do not extend into the radii of the machined and peened areas and do not exceed the maximum dimension shown on the applicable turbine blade drawing. Area between machined ball root and platform edge (exclud- ing the machined groo
48、ves): Areas up to 0.187 inch dimension. (2) 5.1.1.3.6 Machined cooling holes and plug core positioning holes. Machined cooling holes shall be open and functional. Plugged holes and cooling holes shall meet applicable drawing requirements and the following: a. Cooling holes along trailing edge of air
49、foil and plug core positioning holes shall conform to the applicable drawing requirements. Cored passages shall not be blocked or restricted by foreign materials (e.g., core materials, coating powder, base material, etc.) . b. 5.1.2 Type II. 5.1.2.1 Limits for imperfections (visual and fluorescent penetrant). Lim
