NRA Questions and Answers.pdf

1. What are NASA’s rig and test set up capabilities (i.e., surface temperature and pressure limits) for TRL4 and 5 demonstrations for CMC and EBC? Can NASA provide details on the rig and test set up? What are the dimensional requirements for a component for this testing? Can you provide details of temperature instrumentation monitoring options for these rigs?

ANSWER:

NASA EBC/CMC Test Rig Summary

Test Rig Ptotal (atm)

P(H2O) (atm) v (m/sec)

Max Surface Temp

Temp Monitor

Test Piece Dimension

Capabilities

Laser Rig 1 air

>3000F Thermocouple Pyrometer IR Camera

Heat Zone = 1” dia (open system)

1” dia coupons, Sub-components

Simulate component temperature gradient using backside cooling

Mach 0.3 Burner Rig (Jet Fuel)

1 0.1 100 ~2550F Thermocouple Pyrometer IR Camera

Heat Zone = 1” dia (open flame)

Panels, sub-components, components using fixtures

Molten salt corrosion, CMAS test, Erosion test

Can fit any size, however, heat zone is limited to ~1” dia. Can do backside cooling.

QARE Rig

(O2-CH4)

1 0.58 110 >2700F Thermocouple Pyrometer IR Camera

Heat Zone = 1” dia (open flame)

Panels, sub-components, components using fixtures

Have a fixture for 1.5” x 3” airfoil

Recession, Oxidation

Can fit any size, however, heat zone is limited to ~1” dia. Can generate temp gradient using internal/backside cooling

Combustion Rig (Jet Fuel)

30 0.3 30 >2700F Thermocouple Pyrometer IR Camera

Closed system (combustion chamber)

Panels, components using fixtures

Have a fixture for a 3” x 3” airfoil

Recession, Oxidation, Size limited by the ID of the chamber (~5”), Can generate temp gradient using internal/backside cooling

2. Under Combustion Technologies / Combustor Materials, can NASA give an example of what it considers “state of the art” for comparison purposes: particular best-in-class fielded/in-service technologies; or otherwise demonstrated capabilities, even if internal to the contractor?

ANSWER: State of the art would be the material system that is currently used in the contractor’s latest engine in the thrust class identified in the NRA.

3. Under Combustion Technologies / Combustor Materials, can NASA give an example of what it considers to be an adequate successful demonstration of “how to delay the onset of damage” for the CMC/EBC small core combustion liner?

ANSWER: The CMC/EBC combustor liner should be tested under relevant engine conditions to reach TRL 4-5 by the end of the project. Sufficient rig testing of a component or sub-element should be conducted to identify regions of damage, using optical inspection or NDE techniques. Subsequent analysis and/or testing should be used to demonstrate design improvements that will delay the onset of the damage or reduce the extent of the damage compared to baseline concept.

4. What are the material and hardware limitations for CW-22 test section?

ANSWER: The cascade test section typically uses 10-12 blades depending on the inlet flow angle.

The high blade count helps ensure good periodicity. The center three blades (#4, 5, and 6), are typically the instrumented measurement blades. Those blades are not structural members of the facility and have been made from foam, aluminum, or stainless steel. The remaining cascade blades are structural members of the facility, so those have all been manufactured from aluminum or stainless steel.

The endwalls cover the entire cascade and are 2.5-inch-thick aluminum. One endwall has an array of 543 static pressure taps, while the other has probe survey slots. Alternative endwalls are also available for either or both sides. Those can accommodate cast acrylic (Plexiglas) inserts for optical access, and Zn-Se inserts are available within those for IR access.

5. Are there any modifications needed to the test vehicle depending on the test section in cell CW- 22?

ANSWER: Considering the blades as the test vehicle, the pitch is currently fixed at 5.119” and the blade span is fixed at 6.000”. Any deviations from those would require modifications to, or replacement of, the endwalls. Blades with axial chord lengths of 3.9” to 7.1” have been tested previously.

6. Are the techniques (zinc-selenide window inserts, thermochromic liquid crystals, and background-oriented schlieren) considered in the two days testing assumption at typical conditions in the Facility+Rates.pdf provided for CW-22? What is the typical set up time for these methods? How long do they take to execute during the test?

ANSWER: Setup and run times are highly dependent on the particular test configuration and objectives. Thermochromic liquid crystal (TLC) tests tend to require longer run times with at most two flow conditions per day. That is due to the need to slowly sweep the TLC narrow band calibrated crystal over the entire surface of interest by varying the surface heat flux. Steady-state conditions need to be achieved at each incremental step. Infrared (IR) measurements tend to go more quickly but have more difficult optical access through the Zn-Se viewing ports. Setup times for both the TLC and IR measurements tend to be several days. Background-Oriented Schlieren (BOS) measurements also require several days of setup, but data acquisition can be completed in several minutes for each flow condition. The weekly test rates assume time for configuration changes and time for these measurement techniques. CW-22 can test more than two days a week if changes are not necessary.

NASA will be fully covering test costs therefore will cover the deltas.

7. In cell CW-22, can the probes be actuated throughout the entire span at both the inlet and exit to fully characterize the inlet and/or exit flow? Can the probes be actuated aft?

ANSWER: The probe actuators can traverse the entire 6.0” span with appropriate probes. The pneumatic 5-hole pitch-yaw and 3-hole boundary layer probes that have been used previously are cobra probes with a ‘knee’ that allows the probe measurement ports to be located on the probe centerline. The cobra style has the advantage of the measurement ports remaining fixed in space with probe rotation but has the disadvantage of the probe not being entirely retractable. These probes can be actuated from the far endwall to slightly beyond midspan: 0.0 < z/span < 0.55. The actuator has been bored to accommodate nominal 0.25” diameter probes with a thermal shrink tube sleeve applied to electrically isolate the probe from the actuator and the facility. The electrical isolation is used with a touch circuit so the boundary layer probe can be actuated to safely touch the far endwall.

The probe actuator endwall has five survey slots, two upstream and three downstream of the cascade, with the survey slots at various fixed axial locations. Each slot covers three blade pitches. Probes can be actuated in the pitchwise (y) direction, in the spanwise (z) direction, and can be rotated about the probe axis.

8. GRC 52.235-91 Technical Summary (APR 2007)- This requires the offeror to submit, as part of the proposal 1. a hard copy Executive Technical Summary and 2. an electronic copy in Microsoft Word to be provided on a virus-free CD-ROM of the work to be performed under the resultant contract. What is the mailing address to send the hard copy? Does the hard copy have to be received by the Government by the closing date and time of the receipt of proposal or does it have to be postmarked by the closing date and time for the receipt of proposal?

ANSWER: No hard copies are needed. Please disregard this provision.

9. 1852.215-81 Proposal Page Limitations (APR 2015) requires a signed model contract to be submitted as part of the proposal. Will the Government provide a coversheet for the model contract for offeror’s signature or is an offeror provided signed submittal letter on company letterhead acceptable?

ANSWER: We will upload to Beta.Sam the SF33 that will need to be signed.

10. Does 52.217-3 or 52.217-5 apply to the solicitation?

ANSWER: These clauses were included in case options were proposed. They will be removed if no options are on the resulting contract.

11. 52.222-52 is a solicitation clause, was this intended to be included in the solicitation? If so then 52.222-41 would not be included in the contract.

ANSWER: Both of these clauses were added in error, please disregard.

12. Section 10.1.3 states that the model contract is to be signed and returned as part of the proposal, however there is no signature area included in the model contract. Where is it to be signed? What is the purpose for this being signed?

ANSWER: We will upload to Beta.Sam the SF33 that will need to be signed. The purpose to signify that the proposed offeror takes no exceptions to the proposed clauses.

13. Are reps & certs required to be completed at time of proposal solicitation if they are to be completed at time of negotiations as indicated in the Overview?

ANSWER: We will not award until all Reps & Certs are verified; this can be done any time prior to award.

14. The NRA refers to NFS 1835.016-71(d)(4) however this clause no longer appears in the NFS on Acquisition.gov. Please advise or provide a copy of the clause.

ANSWER: Please find all NFS citations and clauses at http://www.hq.nasa.gov/office/procurement/regs/NFS.pdf. The acquisition.gov site does not have a current NFS document.

15. Model contract includes multiple clauses that require 52.245-1 which is not included. Will this be added to the final contract?

ANSWER: Please disregard all government property clauses if there is no government property involved with your proposal.

16. How do we estimate costs associated with rig assembly, hook-ups, troubleshooting, etc. at NASA facilities in our proposals? Will NASA provide specific quotes upon request?

ANSWER: The costs associated with rig assembly, hook-ups, troubleshooting is all a part of the “build up” rates provided. This is an estimate to account for NASA’s initial in-kind contribution and will ultimately be covered by NASA. Therefore NASA will not be providing specific quotes upon request.

17. What level of support (personnel) is included in the facility costs provided?

ANSWER: Facility costs cover the power, consumables, and facility operational personnel. This does not cover any research support.

18. How will the costs associated with use of facilities be accounted for? Will contractors be billed directly for these costs?

ANSWER: Facility costs will be a part of NASA’s in-kind contribution. The rates provided will be used to estimate the in-kind costs. Contractors will not be billed directly for test costs.

19. Is there an estimated award / start date? Can we assume October 2021?

ANSWER: NASA would like to make awards as soon as they can however there is a target date of awarding by Mid 4th Quarter FY21.

20. What is driving the cost increase on W7 and W8 for altitude testing?

ANSWER: The altitude cost increases is due to the additional machines needed to power the altitude exhaust system. So this translates to additional power costs.

21. Is there vacuum capability for bleeds in the "without altitude" option and if so, what is the pressure and flow capability?

ANSWER: No, current bleed systems are operated from the Altitude Exhaust system. W-8 is the only test cell set up for bleed right now.

22. Has NASA had considered (or would consider) a different contract mechanism that would allow for IR&D related to this effort?

ANSWER: At this time, no NASA would not consider any different contracting mechanism.