alt text Research Objectives
The three-stage axial research compressor is based on the rear stages of a Rolls-Royce Indianapolis high-pressure compressor (HPC) design. The compressor is scaled up by a factor of four, while maintaining engine-representative Reynolds numbers and Mach numbers at a design operating speed of 5,000 rpm.


A new design effort, identified as PAX200, incorporates advanced blade design technologies, higher pressure ratios, and increased rotational speeds to 7,860 rpm. Beginning Summer 2016, these modifications will allow higher TRL research in the Purdue three-stage compressor facility.


Current research work with the P3S compressor is funded by Rolls-Royce, NASA, and the GUIde 5 Consortium.



Current work:
  • Advance Technology Demonstrator – D. Matthews & N. Kormanik III
    • Develop performance evaluation and detailed multi-stage flow measurements on novel HPC geometries
    • Inter-stage flow measurements to provide overall performance characteristics
    • Interchangeable blade rows to allow for direct comparison between designs
    • Aerodynamic measurements associated with blade passing frequencies between rotor-stator and rotor-rotor interactions
    • Fast-response measurement techniques, including pressure transducers and thermal anemometry, to measure rotor primary and secondary flows

  • Grand Challenges in turbomachinery forced response – Y. Leng, F. Lou, D. Matthews, & N. Kormanik III
    • Numerical modeling and vibration detection of an embedded rotor stage for Campbell diagram modal crossings (1T, 1CWB, 2CWB) using NSMS and fast-response pressure transducer measurements.
    • Steady and unsteady aerodynamic characteristics associated with changing forcing functions on 1T and 1CWB vibratory modes using reduced and asymmetric vane counts

  • Propagation of inlet distortion though a multi-stage axial compressor – R. Rusu
    • Generate a detailed experimental dataset to validate novel computational approaches for modeling of inlet distortion in multi-stage axial compressors
    • Distortion generators manufacture total pressure deficits upstream of the initial compressor stage
    • Distortion generators are rotated relative to the instrumentation position to obtain detailed circumferential mapping at various loading conditions

  • Optical flow visualization – D. Brune, M. Smyser, & Dr. Terrence Meyer
    • A collaborative effort with the Purdue Optics Lab
    • Utilize advanced particle image velocimetry techniques (PIV) with a pulsed laser, precision optics, seeding particles, and a synchronized high-speed camera to develop three-dimensional velocity fields in the rotor flow path




Specific Instrumentation Capabilities

Pressure taps along the casing and between each rotor and stator row provide information about pressure variation through the flow passage. Multi-element total temperature and total pressure rakes yield performance metrics for the overall compressor, individual blade rows, and stage-by-stage analyses.

Circumferential and Radial Traversing
Independent, circumferentially-indexable vane rows facilitate pitch-wise measurements and vane clocking studies. Additionally, the ability to perform radial traverses with single pressure, temperature, or hotwire probes allows for higher resolution measurements within each blade span.

Particle Image Velocimetry (PIV)
A novel PIV technique has been developed in the embedded stage by introducing incident laser light through the same window used for imaging the flow field. Using this technique, intrusive periscope devices are not required. Ultimately, three-component velocity fields are reconstructed using several imaging cameras through volumetric and tomographic techniques.

Capacitance Probes
Capacitance probes are used to monitor real-time rotor tip clearances. This capability is valuable for health monitoring, but these real-time clearance measurements also reveal tip clearance effects at different speeds, loading conditions, and for different ambient conditions. These data are imperative for future one-to-one comparisons with computational simulations.

Hotwire Anemometry
A unique, dedicated hotwire calibration jet facility allows up to three-dimensional sensor calibrations with precision control of velocity, temperature, and density.

Nonintrusive Stress Measurement System (NSMS)
Optical probes mounted on the compressor casing acquire blade arrival timing information to detect amplitude and phase vibration for each rotor blade
CSTAR
Flow-Visualization
Powder-paint flow visualization is used to highlight the development of stator corner separations and endwall flows in the compressor.
High Frequency Pressure Measurements
High frequency pressure measurements enable identification of flow phenomena such as rotor tip leakage flows and embedded rotor vibration.



Theses
  1. Kormanik, N. J., 2017, "Characterization of Aerodynamic Forcing Functions for Embedded Rotor Resonant Response in a Multistage Compressor," MS Thesis, School Aeronautics and Astronautics, Purdue University.
  2. Aye-addo, P. A. N., 2016, "An Experimental Study of the Effects of Vane Count and Non-Uniform Vane Spacing on Rotor Resonant Response," MS Thesis, School Aeronautics and Astronautics, Purdue University.
  3. Berdanier, R.A., 2015, "An Experimental Characterization of Tip Leakage Flows and Corresponding Effects on Multistage Compressor Performance," PhD Dissertation, School of Mechanical Engineering, Purdue University.
  4. Smith, N.R., 2015, "An Experimental Study on the Effects of Blade Row Interactions on Aerodynamic Loss Mechanisms in a Multistage Compressor," PhD Dissertation, School of Aeronautics and Astronautics, Purdue University.
  5. Monk, D.J.W., 2014, "A Computational Analysis of the Aerodynamic and Aeromechanical Behavior of the Purdue Multistage Compressor," MS Thesis, School of Mechanical Engineering, Purdue University.
  6. Murray III, W.L., 2014, "Experimental Investigation of a Forced Response Condition in a Multistage Compressor," MS Thesis, School of Aeronautics and Astronautics, Purdue University.
  7. Ball, P.R., 2013, "An Experimental and Computational Investigation on the Effects of Stator Leakage Flow on Compressor Performance," MS Thesis, School of Aeronautics and Astronautics, Purdue University.
  8. Brossman, J.R., 2012, "An Investigation of Rotor Tip Leakage Flows in the Rear-Block of a Multistage Compressor," PhD Dissertation, School of Mechanical Engineering, Purdue University.
  9. Berdanier, R.A., 2012, "Design of a Multi-Stage Research Compressor for Cantilevered Stator Hub Clearance Flow Investigations," MS Thesis, School of Mechanical Engineering, Purdue University.
  10. Smith, N.R., 2011, "Experimental Investigation of Vane Clocking Effects on Stall Performance and Unsteady Van Boundary Layer Development in a Multistage Compressor," MS Thesis, School of Aeronautics and Astronautics, Purdue University.
  11. Talalayev, A., 2011, "On the Renovation of the Three-Stage Axial Compressor Research Facility for Compressor Performance Research," MS Thesis, School of Mechanical Engineering, Purdue University.
  12. Salontay, J.R., 2010, "A Computational Investigation of Vane Clocking Effects on Compressor Forced Response and Performance," MS Thesis, School of Mechanical Engineering, Purdue University.
  13. Key, N.L., 2007, "Vane Clocking Effects in an Embedded Compressor Stage," PhD thesis, School of Mechanical Engineering, Purdue University.



High-Speed Compressor Research Laboratory, Purdue University