NASA, George C. Marshall Space Flight Center, Procurement Office, Marshall Space Flight Center, AL 35812

66 -- INSTRUMENTS AND LABORATORY EQUIPMENT SOL 8-W-5-02-79516 POC Contact Patricia Fundum, GP22-D/Contracting Officer This notice constitutes a Request for Quotation (RFQ) for an -- 8-inch Turbine Flowmeter which will be used to accurately measure cryogenic liquid propellants into development rocket engines; All internal flowmeter components (flow straightners, rotor, shaft, and cone) are designed to prevent cavatation at all flow conditions; They must be materially compatible and be capable of measuring liquid hydrogen, liquid oxygen, and KP1 kerosene; All metal to metal contacting parts, where ''fretting'' can occur, are to be dry film lubricated; examples of this are the flow straightener-to-housing contact points and the shaft-to-support points; All clearances and loading of the flowmeter parts are to be designed to prevent any ''Chattering'' which could lead to localized burning in liquid oxygen; Flowmeter will have provisions to prevent rotation of the internal assembly within the housing; All parts of the meter will have positive retention, such as the shaft retaining nut; This nut will be held in place by a lock (tab) washer that is bent around the nut; Manufacturing specifications and tolerances are very critical for the correct operation of the flowmeter thereby reducing the risk of any damage or failure to the development engine--Performance Specifications shall include the following--(1) Length-16 inches, flange face-to flange face--(2) Flange-2-8 hole, 150 #ASA, raised face--(3) Flow Range-60 to 7,000 GPM--(4) Linearity-Better than 0.5 percent over the range of 60 to 6,000 GPM--(5) Accuracy-0.25 percent or better throughout the linear range--(6) Repeatability- 0.25 percent throughout the linear range--(7) Pressure Drop- No greater than 0.4 PSID in liquid hydrogen at a flow rate of 6,000 GPM @ -423 degree F, or 6.4 PSID in liquid oxygen @ -297 degree F--(8) Output-Minimum of 500 millivolts RMS in the linear flow range--(9) Pickoff Coils-Will have two diametrically opposed coils and coils must be able to operate at temperatures of -425 degrees F--(10) Cavatation Limit-Flow meters are to be designed such that cavatation will not occur when flowmeter back pressure drops to 6 PSIG (21 PSIA) in liquid hydrogen @ -423 degrees F--Component Specifications shall include the following--(1) Rotor- Designed to operate at minimum net positive suction pressure (NPSP) requirements set by NASA--The rotor blades are helical (twisted) airfoil design to preclude cavatation at all flow conditions--The final rotor assembly will be dynamically balanced and designed to yield a precision of 0.15 percent or better--Entire rotor is cast out of 304 CRES--Rotor will have imbedded magnets to provide higher signal strength--(2) Rotor Bearings-Must be self-lubricating (dry film)--Rotor bearings must be sized to minimize individual ball loading and therefore reduce wear and heating--Rotor is also designed with safety bearings of AMPCO 18 such that in the event of primary bearing failure, the safety bearings would prevent radial and axial movement of the rotor--Must provide fluid coolant holes to rapidly cool bearings and shaft to maintain assembly preload--In addition these holes help to maintain cooling of the bearings to prevent wear and overheating--(3) Housing-Will consist of one 8-inch pipe, SCH 805, TPL 304L seamless and two 8-inch 150LB ANSI weld neck TP 304L flanges and will have two diametrically opposed bosses to accommodate pickoff coils--(4) Magnets-Will have a magnetic strength of 1000 to 1300 gauss and consists of ALINCO 8--(5) Inspection-100 percent X-Ray and Hydrostst at 300 psig and housing to be designed for 200 psig working pressure with a 4 to 1 safety factor--(6) Vendor Requirements-Vendor must have extensive experience in the manufacturing, calibration, and design to cryogenic turbine flowmeters--Must be an ISO 9002 certified company--(7)Calibration-Ten point water calibration is required on the turbine flowmeter with equivalent Reynolds number calibrations for liquid hydrogen, liquid oxygen, and RP1 kerosene--(8)Other-If vendor performs other design modifications or changes, a rationale of each change shall accompany the quote--The offeror shall provide a description (including manufacturer, brand, and model no.) in sufficient detail to show that the product offered meets the specifications included in this notice--If the end product(s) offered is other than domestic end product(s) as defined in the clause entitled ''Buy American Act-- Supplies,'' the offeror shall so state and shall list the country of origin--The offeror shall state in their offer their size status for this procurement--The SIC code and the size standard for this procurement are 3824 and 500 employees respectively--Questions regarding this acquisition must be submitted in writing--Transmission by facsimile to 205-544-9081 or by Internet e-mail to patricia.fundum@msfc.nasa.gov is acceptable--Quotations are due 30 days after publication of this notice in the Commerce Business Daily (CBD) to the address specified in Item 7 above to the attention of Patricia Fundum/GP22-D-- Selection and award will be made to the lowest priced, technically acceptable offeror--Technical acceptability will be determined by information submitted by the offeror providing a description in sufficient detail to show that the product offered meets the Government's requirement--The period of time expected for the Contracting Officer to solicit/evaluate vendor quotes and issue the purchase order will be approximately 45 days from publication of this notice in the CBD. (0195)

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