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Gas Turbine Propulsion

Transonic Compressor Facility

This is a continuous operation transonic compressor facility that is suitable for fundamental and proof of concept studies of active flow control in the internal flow of turbo-jet engines. The purpose is to provide an environment for the development of flow control concepts at conditions that are closer to those in real engines, and thereby provide a realistic evaluation before moving to more expensive tests in large government and industry facilities.

It consists of a single stage compressor made up of a row of inlet guide vanes (IGV), a compressor-blade rotor and a stator row. The rotor spins on magnetic bearings that can be used to dynamically vary the gap between the tip and casing. Survey rings upstream of the IGV and downstream of the stator row will allow access for internal flow measurements.


The compressor is driven by a 400 hp variable rpm DC motor. The rotor diameter is 18 in., and the hub-to-tip ratio is 0.75. At the maximum 15,000 r.p.m. The inlet Mach number is 0.65 and the tip Mach number is 1.1.








Transonic Turbine Facility

This transonic turbine facility was designed and built for fundamental and proof of concept studies of active flow control in gas turbine engines. The laboratory is designed to fill the gap between typical facilities found in universities, and those that exist in DoD laboratories.

The purpose was to provide an environment for the development of performance enhancing concepts at conditions that are closer to those in real engines, and thereby provide realistic evaluation before transitioning to more expensive tests in large government and industry facilities. The general characteristics of the facility are continuous transonic operation, a loading coefficient greater than 3, a flow coefficient of no less than 0.5, a pressure ratio of up to 2.2, and a relatively large mean diameter that is comparable to some smaller engines.






Transonic Tubine Components

Other special features include magnetic bearings that allow azimuthal variations in tip-gap clearance that is a major factor in turbine-stage performance and one of the primary subjects of active flow control in the facility, significant access for detailed internal flow surveys, and the capability for injecting cooling flows in stationary and rotating parts.




Hot Annular Nozzle CascadeHANC


The Hot Annular Nozzle Cascade facility is a non-rotating turbomachiery rig designed to test the first stage turbine nozzle of a jet engine. It is the only non-rotating turbomachinery facility at Notre Dame. A system of two centrifugal compressors serve to move air through the ductwork and test section with the objective of matching the design conditions of the real jet engine at the turbine inlet during cruise. A key feature of the facility is the operating air temperature of 700 degees F. A series of valves, flow control mechanisms, auxiliary blower systems and high-grade insulation ensure safe and continuous operation of the facility.

Research Objective

The primary objective of this research is to replicate nozzle inlet temperature profiles seen in real engines. Auxiliary blower are used to inject cooler air at the end walls and to create a variety of inlet temperature profiles. The facility provides the capability to incorporate engine test articles scaled in size in order to better understand the detailed flow physics around the cooled or uncooled turbine nozzle vanes. The Facility also provides the capability to match turbulence intensity levels found at the exit of the combustor and at the inlet of the fire stage nozzle in the real engine.



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