Gas Turbine Power System
Overview
Buyer
Place of Performance
NAICS
PSC
Set Aside
Original Source
Timeline
Qualification Details
Fit reasons
- NAICS alignment with historical contract wins in similar service areas.
- Scope strongly matches core technical capabilities and delivery model.
Risks
- Past performance thresholds may require one additional teaming partner.
- Potential clarification needed on staffing minimums before bid/no-bid.
Next steps
Validate eligibility requirements, assign capture owner, and schedule partner outreach to confirm teaming strategy before submission planning.
A complete gas-turbine power system to consist of an engine designed and manufactured for engineering education. Engine must utilize a centrifugal flow compressor, reverse flow annular combustor and an axial flow turbine stage. Engine to be of current manufacture and consisting of all new components. All engine components either vacuum investment cast or precision CNC machined. All high-heat components manufactured from 17-4 ph stainless steel, Inconel� 718 or CMR 247 Super Alloy. Traceable and verifiable material to be used throughout engine. All elements comprising the system to be contained in a rigid steel chassis mounted on rolling castors. All system metal surfaces to be stainless steel, anodized or powder coated to promote durability and wear resistance. Complete system not to require any permanent facility modifications or additions, self-contained. Engine situated behind transparent protective shields allowing clear view during operation. Operator capable of manual control throughout entire range of operation. Operator panel to consist of digital TIT, EGT, and RPM indicators, analog oil pressure, engine pressure ratio, fuel pressure and air pressure gauges, keyed master, green start, red stop and T-handled power control lever. System to be equipped with calibrated transducers and thermocouples capable of measuring compressor inlet, compressor exit, turbine stage inlet, turbine stage exit and thrust nozzle exit temperature and pressures, fuel flow, thrust and engine compressor / turbine rotational speed. Engine thrust to be measured by a load cell permitting direct indication of thrust value. To be supplied with a USB based digital data LabView acquisition system complete with computer and user configurable LabView data acquisition software capable of measuring and recording analog, digital and frequency signals. Fully automatic engine start and operational health monitoring system provided with LCD status readout and cumulative run- time and cycle count. Representative engine components and technical data optionally available for teaching use and training aids. Manufacturer to guarantee spares availability and provide technical support services for core engine and power system. Provided with a comprehensive Operator?s Manual. Provided with summary operating checklist for all operating conditions. Provided with safety instruction to address all operating conditions. Power:120V single-phase 60Hz. Design Maximum Thrust: 40 lbf (178 N). Approved Fuels: Jet A,A-1, B; JP-4, 5, 8; Kerosene, Diesel, Fuel Oil #1 or #2. Compressor Type: Single Stage Centrifugal (Radial Outflow). Approved Oils: MIL-PRF-23699F-STD, Sensors(Preinstalled and Calibrated) Compressor Inlet Temperature and Pressure (T1/P1) Compressor Exit Temperature and Pressure (T02/P02). Turbine Stage Inlet Temperature and Pressure (T03/P3) Turbine Stage Exit Temperature and Pressure (T04/P04). Thrust Nozzle Exit Temperature and Pressure (T05/P05). Fuel Flow Thrust Engine Rotational Speed (RPM). Digital Turbine Inlet Temperature (TIT). Digital Exhaust Gas Temperature (EGT). Digital Engine Rotational Speed (RPM). Analog Oil Pressure. Analog Engine Pressure. Analog Air Start Pressure. Design Maximum RPM: 87,000. Engine Compression Ratio: 3.4, Engine Pressure Ratio: 30.0. Exhaust Gas Temperature: 1328 � F (720 � C)