Statement of work.docx

Statement of Work

F112 THRUST STAND AND INSTRUMENTATION

Title: F112 THRUST STAND AND INSTRUMENTATION Document Date: 25 June 2026

1. Scope: This Statement of Work is for a F112 Thrust Stand and Instrumentation delivered on a firm fixed price contract operated as a CLIN (Contract Line-Item Number). The delivered hardware is for conducting research & development on a Williams F112 engine. This Statement of Work is intended to be performance‑based; the Government specifies required capabilities and outcomes, and the contractor is responsible for the detailed design and methods used to meet or exceed these requirements.

1.1 Background: Advancing engine technology is typically a slow process of very slight improvements. In order to make significant changes to performance, large steps must be taken to integrate advanced technology. AFRL in conjunction with AFIT have advanced rotating detonation engine technology to the point of being able to be integrated into large Air Force systems such as primary combustors and afterburners. These detonation engines have proven themselves in other arenas such as the T63 engine tests and the augmenter studies. To advance these capabilities further, a test bed engine is required. The Air Force has multiple Williams F112 engines in store that would provide and foundation to integrate these new technologies, however the engines alone will not provide the data. The F112s require a thrust stand, data acquisition platform and large array of sensors to evaluate the performance of the engines before and after modification. To that end, the investment in these support systems for the engine is required to make the necessary advancements in engine performance offered by detonation engine technology.

2. Applicable Documents All documents invoked in the requirements section of the SOW must be listed in this section by document number and title.

3 Requirements/Salient Characteristics: The minimum requirements for the F112 Thrust Stand and Instrumentation to be delivered include the following:

Thrust Stand:

1- Structure: The thrust stand must be rated to thrust loads of not less than FThrust = 5,000 lbf and a static weight rating of no less than Fstatic = 15,000 lbf. The nominal dimensions of the stand should be approximately 10 feet in length and 2 feet in width with the engine centerline height between 30-40”.

2- Dynamics: Flexures must be used to dissociate the engine stand from the ground, ensuring appropriate elasticity and fracture strength of selected material. Linear bearings and similar devices will be avoided in this subsystem due to stiction and similar errors.

3- Measurement: The stand must be capable of measuring the full scale of the thrust load (both directions) with a load cell error <0.1% Full Scale. This measurement must be taken on the axis of the engine’s centerline. Calibration of this measurement must be performed via known loads at the fore end of the engine to account for errors introduced from instrumentation and other hardware.

4- Operability: The thrust stand must be able to integrate an F112 engine and corresponding hardware such that maintenance is feasible without complete disassembly (via rails, pivots, etc.) A modular design allowing forward and aft engine mount locations is necessary to accommodate future hardware (e.g. inlet or augmenter) without significant modifications to the stand.

Instrumentation:

1- The contractor shall obtain and deliver one new operational Williams F112 engine suitable for ground testing in accordance with this SOW. The engine shall include mounts adapted to the thrust stand rails. Upon Government acceptance, the Williams F112 engine shall become property of the Department of the Air Force and be conveyed to AFIT.

2- Provide a stand-alone (not for vehicle) engine controller. This shall include the communication and controls for the engine interfaced through LabVIEW.

3- Provide a National Instruments PXI data acquisition system with a minimum of:

a. Chassis: 24 GB/s, 18 slot

b. Controller: 2.8 GHz, 4 core, 32 GB Memory

c. Low Speed Analog Input: 144 Diff Channels, two cards

d. Thermocouples: 64 TC Channels, two cards

e. High Speed Analog Input: 32 Diff Channels, two cards

f. Analog Output: 8 Channels (V/mA), one card

g. Bridge: 8 full, half, quarter channels, one card

h. Digital I/O: 144 channels 4- Provide 64 low speed (<100kHz) pressure transducers as required for instrumenting engine to evaluate operation and component efficiencies.

5- Provide 8 high speed (>500 kHz) pressure transducers up to 500psig.

6- Provide 4 high speed (>500 kHz) 3 axis accelerometers or equivalent.

7- Provide 64 thermocouples as required for instrumenting engine to evaluate operation and component efficiencies.

8- Provide 16 Kiel probes as required for instrumenting engine to evaluate operation and component efficiencies.

9- Provide a fuel boost pump as needed.

10- Provide power supplies as needed.

11- Provide fuel lines compatible with thrust stand functionality.

12- Provide provisions for active monitoring of compressor/fan stall in case of additional backpressure.

13- Plumbing hardware adapters shall be compatible with Swagelok fittings.

14- Instrument the engine to provide redundant component efficiency measurements (not less than two measurements for each required property) without interfering with engine performance significantly (all instrumentation must fit with less than 5% blockage of any flow area).

Technical Data:

1- The contractor shall be responsible for obtaining and using all technical data, manuals, and interface information necessary to safely mount, operate, instrument, and maintain the Williams F112 engine on the thrust stand. The Government does not commit to furnishing engine technical data beyond what may already be available as Government property under separate arrangements.

Figure 1: Williams F112 Engine (image from Wikipedia)

Testing and Training Requirements: The engine must come with an operating procedure. Accompanying instructions for the thrust stand and DAQ must also be supplied.

Safety:

All standard lab safety measures apply, including FOD screen.

Period Of Performance: The contractor shall deliver a complete system no later than 18 months after contract approval.

Delivery: The supplier shall properly ship the system to the Air Force Institute of Technology at WPAFB, OH (45433) The complete system, including the Williams F112 engine, thrust stand, engine controller, data acquisition system, and all instrumentation and accessories provided under this SOW, shall become Government‑owned property upon acceptance. All shipping costs to include insurance will be included in contractor’s proposal. Great care using standard, approved packaging methods shall be taken.

Warranty: Free from defects in material and workmanship for the engine stand and instrumentation, under normal and proper use in accordance with manual, for the period of time of one year after receipt.

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