SATPC0036322 Tab 04 4 SOW.pdf
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- Solicitation number
- 80NSSC24880327Q
About this file
This document is a Statement of Work (SOW) for the additive manufacturing of Inconel 718 parts for NASA's CE-13 combustion facilities. The vendor shall fabricate the listed Inconel 718 parts using laser powder bed fusion or selective laser melting processes. NASA will provide the required drawings and 3D geometry files. The vendor must meet specific requirements for material certification, density, heat treatment, dimensional inspection, and tensile testing. The deliverables include both machined and printed parts, with quantities and delivery timelines provided. Pricing is required to be broken out by manufacturing process, heat treatment, and tensile testing. The related federal contract opportunity is a solicitation for the additive manufacturing of material test hardware for the CE-13 facility, with NASA as the contracting agency.
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| File | Type | Posted |
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| SATPC0036322 Tab 10 RFQ Open Market Template.pdf |
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Additive Manufacturing of Inconel 718 Hardware for Combustion Test Facilities
The National Aeronautics and Space Administration (NASA), specifically NASA Glenn Research Center (GRC) has a need for the additive manufacturing of Inconel 718 parts for tests that will take place in the CE-13 combustion facilities.
Task 1, Inconel 718 Parts for CE-13 facility
1. Vendor shall fabricate all listed Task 1 parts and quantities as noted in the Deliverables, using Inconel 718 additive manufacturing material and laser powder bed fusion or selective laser melting.
2. NASA shall supply vendor with all required drawings and 3D geometry files for construction. Vendor may alter NASA provided geometry as required to be compatible with build process and material as long as final part requirements are not impacted. Example: adding support material at the part/build plate interface is allowed; adding internal supports that cannot be removed is not allowed.
3. The material shall be Inconel 718 powder supplied by vendor. Certificate of Conformance to be provided to NASA for the material batch(es) used in the build.
4. Density of SLM Inconel 718 material samples shall be a minimum of 99.2% prior to any post-processing heat treatments or Hot Isostatic Pressing (HIP).
5. All parts to be heat treated per drawing specifications.
6. The parts shall be co-fabricated (same build). If part count exceeds single build plate capacity, multiple build plates may be used, however identical parts shall be constructed on the same build plate. Vendor shall alert NASA GRC Technical Point of Contact (Bryan Harder) of deviation from this requirement and document which parts were constructed in which batch.
7. Powder removal via vibration and ultrasonic cleaning.
8. Post machining shall be completed on parts per drawing requirements. All dimensions and tolerances shown as machined features are applicable to the final part in the heat-treated condition.
9. Dimensional inspection using bench tools with an expected tolerances per the included drawings.
Dimensional inspection report to be provided electronically to NASA GRC Technical Point of Contact (Bryan Harder) as soon as possible after build and prior to shipment of parts.
10. Vendor shall print multiple tensile test samples with each build plate, subject samples to the same heat treatment regime as final parts, and tensile test at least one sample from each build plate to failure. Results from tensile test to be provided to NASA GRC Technical Point of Contact (Bryan Harder). Samples must show compliance with minimum tensile and/or yield strength indicated on applicable drawings.
11. 1 piece of the print from each build plate 3D scanned and overlayed with a CAD model to measure profile tolerance. Profile tolerance shall be adhered to per the applicable drawing. Vendor to provide report of profile tolerance findings and any deviations outside of drawing indicated tolerances shall be reported to GRC Technical Point of Contact (Bryan Harder).
12. Vendor shall provide a basic build package including any build anomalies and data relative as evidenced of process validation under documentation required by AS9100, ISO9001, or similar standard.
13. Any build irregularities that will detrimentally affect the properties of the final parts or any out of tolerance conditions should be reported promptly to GRC Technical Point of Contact (Bryan Harder) for potential dispensation.
14. The following items shall be broken out separately in a formal quotation:
a. Cost for additive manufacturing per part number
b. Cost for post-machining per part number
c. Cost for heat treatment, all parts
d. Cost for tensile testing
Summary of Deliverables:
Task Drawing number (drawing title) – part file name Material QTY Delivery
Date
1 210201MRA256 (CE-13 CMC RETAINER MACHINED) -
210201mra256_retain_mach.prt Machined/heat treated 4 8-10 weeks
* 210201MRA257 (CE-13 CMC RETAINER PRINTED) - 210201mra257_retain_print.prt Inconel 718 “ “ 1 210201MRA258 (CE-13 CMC CARRIER MACHINED) - 210201mra258_carr_mach.prt Machined/heat treated 4 8-10 weeks
* 210201MRA259 (CE-13 CMC CARRIER PRINTED) - 210201mra259_carr_pr.prt Inconel 718 “ “
*Indicates parts that are additively manufactured. The part number 1 less than indicated is the associated machining/finishing drawing.
Shipping
1. Vendor shall provide a cost line item for shipping all completed components to customer in formal quotation.
2. Vendor shall send completed hardware to:
Bryan Harder 21000 Brookpark Rd, MS 106-1 NASA Glenn Research Center Cleveland, OH 44135
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