SOLICITATION NOTICE
A -- DISK SUPERALLOY (ME3) SPECIMEN MACHINE AND TEST PROCUREMENT
- Notice Date
- 5/3/2005
- Notice Type
- Solicitation Notice
- NAICS
- 541710
— Research and Development in the Physical, Engineering, and Life Sciences
- Contracting Office
- NASA/Glenn Research Center, 21000 Brookpark Road, Cleveland, OH 44135
- ZIP Code
- 44135
- Solicitation Number
- NNC05103299Q-1
- Response Due
- 5/20/2005
- Archive Date
- 5/3/2006
- Description
- NASA/GRC has a requirement for Disk Superlloy (ME3) Speciment Machining and Testing. The following SOW provides further requirement and quantities or this procurement. Statement of Work Disk Superalloy (ME3) Specimen Machine and Test Procurement Period of Performance June 2005 ? December 2006 A) CREEP machine, then test: Please quote on 8 creep specimens to be EDM blanked from a disk section, machined to a mutually agreed specimen configuration having a gage diameter of 0.25? and maximum length of 3.50? with shot peened threads, then creep tested according to ASTM E 139, the test setup instructions below, 500 hour test time assumed at 1300F for quoting. Creep test procedures/steps, in accordance with ASTM E 139: 1. Shot peen the threads. 2. Measure gage diameter, gage length between radius corners, and overall length using pre-agreed procedures. 3. Perform alignment check and cert on each creep frame to be used. Mount in the creep load frame using your standard grips. 4. After mounting and fully aligning specimen and extensometer in the load frame and furnace, preload the specimen to 50% of the test load. 5. Complete any packing of the furnace with insulation. 6. Gently download to between 15 and 10% of the test load for heat up. 7. If at any time after step 3 the load goes below 10% of the applied load, must go back to step 3 and 50% preload at room temperature. 8. Equilibrate minimum of 1 hour at test temperature, until the strain is constant over a 15 minute interval. This should not require more than 3 hours. 9. At the start of the test, use consistent load-up rate and record data at 1 min. intervals, then lengthen intervals as appropriate. 10. Stop test when it reaches 500 hours, cool under load. B) TENSILE machine, then test: Please quote on 11 tensile specimens to be EDM blanked from a disk section, machined to specimen configuration 4013195-001P01, which uses 1/4-20 grip threads. Please include shot peening of the grip threads on all machined specimens. Then tensile test per ASTM E 21 at elevated temperatures to be specified 1000F to 1400F. Tensile test procedures, in accordance with ASTM E 21: 1. Measure gage diameter at mid-gage, gage length between radius corners, and overall length using pre-agreed procedures. 2. Note no gage marks or divot marks should be applied to this notch-sensitive material. 3. Keep on the extensometer until about 2% strain while testing at 0.5% per minute. 4. Remove extensometer before going to stroke control to specimen failure at a faster crosshead motion of 0.05 times the adjusted length of the gage section per minute (5% per minute approximated strain rate). C) FATIGUE CRACK GROWTH machine: Please quote on 5 FCG specimens to be EDM blanked from a disk section, inertia welded with contractor supplied IN718 grip ends, then machined to specimen configuration NASA Kb bar fatigue crack growth specimens. Please ship all Kb specimens as soon as available. D) NOTCHED LOW CYCLE FATIGUE machine and test: Please quote on 19 NLCF specimens to be EDM blanked from a disk section, inertia welded with contractor supplied IN718 grip ends, then machined to specimen configuration NASA NLCF. NASA NLCF specimen tests These will all have a 90 second dwell at maximum load in each cycle, assume 100 h total test time: 1. Shot peen the shanks with the gage protected from damage. 2. Use an optical comparator to measure notch radius and notch diameter, 5 readings each, then clean with ethanol and cloth. 3. Use at least two thermocouples in the gage section: control from one, comparing their temperatures after heat up and equilibration. 4. First run 10+ cycles at about 10% of the load range (R=0) to check the test system?s control stability. 5. Start test using an agreed startup procedure which gradually increases the load range to the target value while avoiding overloads. 6. 90 second dwell tests: run to failure or directed interruption, assume 100h total time duration for each test in the quote. Place fracture specimen halves in the plastic tube with the button ends butting together, fracture surfaces protected from metal contact. E) LOW CYCLE FATIGUE machine and test: Please quote on 18 specimens to be blanked, machined, and then LCF tested as described below. MACHINING: The vendor will have to first machine specimen blanks from ME3-type nickel-base superalloy disk material supplied by NASA, by electro-discharge machining as per NASA drawings. The vendor shall then machine specimens using the specimen drawings listed below. The shanks of all LCF specimens shall be shotpeened, while the gage sections are masked for protection from shotpeening. The vendor shall need to supply and inertia weld IN718 superalloy grip ends onto disk material blanks for subsequent machining of the make-up specimens. The final specimens shall be PGR-3-1997. The drawing list: Drawing No. Description 1) EDM Blank Electro-discharge machining of blank from disk forging, cost per square inch 2) 4013195-731P03short Make-up inertia welded specimens (vendor to furnish IN718 grip ends) 3) PGR-3-1997 0.40? gage dia. LCF specimen with button-head ends from ?731P03short These standard drawings should currently be on file at the vendor?s location. All test material scrap shall be returned to NASA, identified according to forging blanking layout and identification number. The machined specimens shall be inspected after machining for meeting drawing specifications, and any discrepancy shall be communicated immediately for resolution. Each specimen shall be separately packaged according to specimen identification number. The specimens after testing shall then be shipped to NASA Glenn Research Center, 21000 Brookpark Rd., Cleveland, OH 44135 (attn. Tim Gabb M.S. 49-3). Low Cycle Fatigue Tests - The vendor shall run strain-controlled or load-controlled fatigue tests according to the latest ASTM E-606 standards. Stress-strain hysteresis loops at periodic cycles as well as tabulated results including initial and half life values of modulus, maximum and minimum stresses, and inelastic strain range shall be reported as appropriate; as well as expansion strain, initiation life, and failure life. The tables shall be provided as hard copies and on a computer disk as Excel spread sheets. Tested specimens and remnant material from machining shall be returned. Then for elevated temperatures up to 1300F please quote quantity discounted unit price for E-606 strain-controlled fatigue tests and load-controlled fatigue tests of these specimens. The test quotes should be provided for tests assumed to each run a total time duration of 24 hours, using the procedures described below: 1. Shot peen the shanks with the gage protected from damage. 2. Measure gage diameter, clean with ethanol and cloth. 3. Use at least two thermocouples in the gage section: control from one, comparing their temperatures after heat up and equilibration. 4. First run 10+ cycles in load control, then 10+ cycles in strain control, both at about 0.2% strain range (R=0) to check extensometer stability and the test system?s control stability. 5. Start test using an agreed startup procedure which gradually increases the strain range to the target value at 0.05 hertz while avoiding overstrains. Then continue the test at a frequency of 0.33 hertz for 6 hours. Then: a. If max. and min. cyclic stresses are stabilized, please switch to load control at 10 hertz with the same max. and min. cyclic stresses, run to 5x106 cycles runout. b. If cyclic stresses are still relaxing by more than 1 ksi per 500 cycles, continue until stabilized for mode switch for up to 2 more hours. Call if not yet stabilized. 6. Run test to failure, agreed tensile load drop, or agreed runout cycles. Place fracture specimen halves in the plastic tube with the button ends butting together, fracture surfaces protected from metal contact. Please quote assuming material for at least 10 specimens would be supplied at a time. A delivery time of 8 weeks after receipt of material is desired. Deliveries of partial quantities are encouraged and will be acceptable for meeting delivery time requirements in large orders. This notice is a combined synopsis/solicitation for commercial items prepared in accordance with the format in FAR Subpart 12.6, as supplemented with additional information included in this notice. This announcement constitutes the only solicitation, which is issued as a Request for Quotation (RFQ); quotes are being requested and a written solicitation will not be issued. The Government intends to acquire a commercial item using FAR Part 12 and the Simplified Acquisition Procedures set forth in FAR Part 13. Questions regarding this acquisition must be submitted in writing to the Contracting Officer at Irene.Cierchacki-1@nasa.gov, no later than May 13, 2005, 4:30 EST. It is the quoter's responsibility to monitor this site for the release of amendments (if any). Potential quoters will be responsible for downloading their own copy of this notice, the on-line RFQ and amendments (if any). An ombudsman has been appointed - See NASA Specific Note "B". Any referenced notes may be viewed at the following URLs link below.
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