Gas Turbine Power System W911S225U1171
Summary
AI-generated · Aug 24, 2025A complete gas-turbine power system designed for engineering education is being procured. The engine must be a current-manufacture, all-new component system featuring a single-stage centrifugal compressor, a reverse-flow annular combustor, and an axial turbine stage, with all high-heat parts made from approved alloys. It must be housed in a rigid steel chassis on rolling castors, with stainless, anodized, or powder-coated surfaces, and a transparent shield for direct viewing. The system should be self-contained with no required facility modifications and allow manual control throughout its operating range, including an operator panel with digital TIT/EGT/RPM indicators and various analog gauges, a master and start/stop controls, and a power lever.
Instrumentation and data capability are key: calibrated sensors and thermocouples must monitor compressor inlet/exit, turbine stage inlet/exit, thrust nozzle exit temperatures and pressures, fuel flow, thrust, and RPM, with thrust measured by a load cell. It must include a USB-based LabView data acquisition system (computer and configurable software) capable of capturing analog, digital, and frequency signals, plus a fully automatic start and health-monitoring system with an LCD status readout and cumulative run-time and cycle count. The package must include spare parts and technical support for the core engine and power system, a comprehensive operator’s manual, operating checklists, and safety instructions. Specified performance and fuels include up to 40 lbf thrust, max 87,000 RPM, 3.4:1 compression ratio, EPR of 30.0, exhaust temperature around 1328 °F, and operation with Jet A/A-1, B, JP fuels, kerosene, diesel, or Fuel Oil #1 or #2, powered by 120V single-phase 60 Hz.
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)
From Combined Synopsis/Solicitation posted on Jul 16, 2025Notice history
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