RFQ_80NSSC18Q0959_Statement_of_Work.pdf

Statement of Work NASA One-Sided Ejector Nozzle Thrust Test

Updated July 18, 2018

Background The NASA Supersonics Project has been studying lightweight and simple ejector nozzles to provide 3-

6 dB attenuation of jet noise that may be needed by today’s modern turbofan engine cycles proposed for use on a next generation supersonic aircraft. A simplified geometry has been tested in the NASA Glenn Research Center CW17 test cell. It is desired that a thrust measurement be obtained on this nozzle test hardware. This nozzle will be used as a validation case for CFD based thrust calculation so a high accuracy number is desired.

What is the duration of the tests?

Duration is up to the vendor and can depend on the vendors facilities and capabilities, but is anticipated to be between 2 days to 2 weeks.

Why are the tests not being done at GRC?

GRC currently does not have a thrust measurement test rig for nozzles of this size. Test data is requested for comparisons to GRC analysis and potential future test capability.

Requested Period of Performance NASA desires that the testing be completed by December 1 2018.

Provided Data and Hardware

1. NASA shall provide test nozzle hardware for the One-Sided Ejector (Figure 1).

a. Exit area of primary nozzle (Figure 3a) is 3.54 square inches. The upstream flange of assembly has nominal 6” inner diameter. Assembly is stainless steel and weighs 28 pounds.

b. Tab strip (Figure 3b) is formed from 0.014” thick stock.

c. Ejector box (Figure 3c) is fabricated from ½” thick aluminum sheet stock, bolted together. The ejector box has previously been attached to the primary nozzle using external supports (Figure 2). Plug spacers in sidewall slots define variable ejector geometry.

2. NASA shall provide CAD solid geometry in STEP or IGES format for all provided test hardware.

Deliverables

1. The proposer shall measure axial thrust of the One-Sided Ejector, and all flow parameters required to deliver nozzle thrust coefficient curves for four geometric configurations of the Ejector, defined in Table 1.

2. The proposer shall measure each geometric configuration at 6 unheated flow conditions, given in Table 2.

3. The proposer shall deliver documentation demonstrating the test facility accuracy in axial thrust coefficients for this size nozzle at the flow conditions given in Table 2 is less than 0.5% as demonstrated by conformance to published ASME nozzle thrust measurements.

4. The proposer shall deliver all measured data (mass flow, nozzle inlet conditions, atmospheric conditions, nozzle static pressure instrumentation, and thrust data) in printed report and electronically in Excel .csv format or equivalent.

5. The proposer shall provide detailed photos of the test setup at the proposer’s facility.

6. All NASA-provided hardware will be returned in original condition, with the exception of the tab strip, which will be left attached to nozzle for inspection.

Table 1 Geometric configurations (baseline with no tab strips, two configurations with tab strip, and one case with tab strip and divergent upper plate). Definitions of parameters given in Figure 4.

Configuration Tab strip G (inch) H (inch) 1 no 0.249±0.005 0.900±0.005 2 yes 0.235±0.005 0.900±0.005 3 yes 0.380±0.005 1.050±0.005 4 yes 0.170±0.005 1.080±0.005

Table 2 Flow conditions for nozzle flow, plenum total pressure divided by ambient pressure.

index Pt/P∞ index Pt/P∞ 1 1.40 4 2.10 2 1.70 5 2.50 3 1.90 6 3.00

Additional Work Required:

The following preparatory work will be required for the proposer to meet the Deliverables:

1. The proposer shall design and fabricate an adaptive flow section between the contractor-provided thrust measurement facility and the NASA test article.

2. The proposer shall provide means of attaching tab strip to primary nozzle (Figure 3). Method of attachment may require destruction of tab strip for removal. Tab strip attaches with button-head screws, but spot welding will be required to assure geometric fidelity.

3. The proposer shall design and fabricate means of attaching the ejector box (Figure 3c) to the primary nozzle. The attachment must be made such that the ejector box may be repeatedly attached and detached. Alternatively, parts of the ejector box may be redesigned and fabricated as part of the attachment process, maintaining internal flow lines, with NASA approval.

Figures:

Figure 1 One-Sided Ejector nozzle assembly.

Figure 2 Photographs of One-Sided Ejector assembly as tested at NASA GRC.

(a) (b) (c) Figure 3 Subassemblies: (a) Primary nozzle, (b) tab strip, (c) ejector box.

Figure 4 Sketch to define ejector parameters.

Instructions for Quotation Quote shall contain

1. Cost of Deliverables as specified in Statement of Work,

2. Documentation of past performance in nozzle thrust measurements, including description of calibration standards to be used in NASA test, confirming proposers’ capability of meeting required accuracy,

3. Schedule for performance of testing.