RESEARCH AREAS
Unsteady Turbine Cascade Aerodynamic
Research and Heat Transfer
Unsteady Boundary Layer Transition
Research and Heat Transfer
Unsteady Boundary Layer Transition Modeling
Turbine
Engine Performance, Aerodynamcis, and Heat Transfer
Dynamic Simulation of Gas Turbine and Jet Engines
| Research Facilities |
| TPFL has several modularly structured and multi-purpose research facilities for investigating aerodynamic and heat transfer relative to turbomachinery performance and flow physics. These are: |
| 1. Three-stage research turbine for interstage aerodynamics, individual loss measurements, code validation |
| The overall layout of the test facility and the major components of the research turbine facility at TPFL as well as the composite picture of the entire facility are shown in Figs. 1, 2, and 3. The versatile design of the turbine enables investigating different turbine types and blades. Figures 4 and 5 shows two different type of blades investigated recently. Figure 4 shows a rotor with 3D-shrouded blades for a HP-turbine. On this rotor, detailed efficiency, performance, and flow research test were conducted. However, Fig. 5 exhibits, a set of fully cylindrical HP-blading with shrouds. Comprehensive efficiency, performance and flow field measurements were performed on both rotors and the results were compare with each others. The versatile turbine design allows clocking the stator rings individually and externally without opening the turbine. The clocking system is shown in Fig. 6. As the figure shows, each stator ring is connected with a pneumatic power cylinder that allows a continuous clocking of the stator ring |
| 1.
Three-Stage Turbine Engine Research Facility return to top |
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Fig. 1: The research
turbine facility with its components, the circumferential traversing
system (9) is
driven by another traversing system sitting on a frame and is perpendicular
to this plane.
Three-Stage Turbine Research Turbine Facility
TPFL, Turbomachinery Performance and Flow Research Laboratory
Prof. Dr.-Ing. M.T.Schobeiri
Fig. 2. Composite picture of the research turbine facility in operation. Visible are: PSI-scanners, traversing controller (red), pneumatic clocking system, combined total temperature, total pressure rakes (top, in two protecting tubes), radial and circumferential traversing system (on top of the frame), Prof. Schobeiri and his Ph.D. students E. Johansen (middle) and Mr. P. Chakka (left). |
Rotor unit and Clocking System
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Fig. 3: Front view of the turbine rotor with 3D-bowed, hydraulic clocking system
| INTER-STAGE TRAVERSING |
Circumferential and radial traversing occurs fully automatically by implementing a schedule file into the data acquisition system (DAS). Figure 5 shows the schematic of the traversing kinematics. |
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Fig
4. : Interstage traverse and prescribed kinematic schedule for traversing
system. NC = umber of
points in circumferential direction, NR = Number of points in radial
direction.
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Figure
5: Total pressure contours at station 4 for a rotor with 3D-bowed blades
(left) and a rotor with 2D blades (right) at the same rpm. Note
the reduction of the secondary flow losses for the lade compared to
the 2D-one. Operating conditions: (1) Inlet conditions the same ,
(2) Staor clocking position is the same for both cases.
2.
Unsteady Turbine Cascade Research Facility
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to top
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Fig.
6: The facility consists of a large centrifugal fan, a large silence
chamber, an inlet nozzle, unsteady test section with rods attached
to two parallel translating belts to generate periodic unsteady
flow. The test section incorporates 5 LPT-blades, one instrumented
with 176 surface mounted hot film probes, one with static pressure
tabs and two additional blades to maintain periodicity. The test
section bed can move up- and downward for height adjustment. Two-dimensional
periodic unsteady wake flow is simulated by the translational
motion of the wake generator shown in Fig. 6. A series of cylindrical
rods are attached to two parallel operating timing belts driven
by an electric motor. The belts of length 5000 mm span over five
shaft-pulleys arranged around |
3.
Unsteady Boundary Layer and Heat Transfer Research Facility
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to top
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|
Fig.
7: 1)Plexiglass side wall, 2) Concave wall, 3) Curved plate instrumented
with static pressure taps for static pressure measurements and
surface liquid crystal for heat transfer measurements, 4) Hotwire
probes, 5) Guidance for bottom traversing system, 6) Top and bottom
traversing systems, 7) Wake generator units, 8) Gear, 9) Electric
motor to drive the wake generator, 10, 11) Vernier for angular
and longitudinal adjustment of the curved plate. |
| RESEARCH CAPABILITIES |
| 1. Turbine Efficiency, Performance, and Flow Research Relative to Gas Turbine , Steam Turbine Blades: |
| Development of new generation
of high efficiency turbine blades. This task includes: |
| Secondary flow, tip leakage aerodynamics
and heat transfer. Stator hub and rotor tip secondary flow and heat transfer Efficiency and interstage flow measurement |
| Total to static, total to total efficiency
test of new turbine blades |
| Efficiency, performance, and flow measurement of
blades with particular surface roughness |
| Clocking, its effect on efficiency
and turbine flow field Partial admission efficiency and performance measurements Interstage flow measurements Rotor-stator interaction for code validation Surface shear stress measurement on stationary blades with hot films |
| Cooled Gas Turbine Blades: Heat
Transfer, Aerodynamics, Performance using PSP and TSP-Technology Stator blade heat transfer measurement Staror film cooled aerodynamic measurements Rotor film cooled aerodynamic measurements Stator ring, shroud heat transfer measurements Rotor cylinder heat transfer measurements Rotor-stator interaction, by applying hot film on stator and rotor blades. Total to static, total to total efficiency test of new cooled turbine blades |
2. Turbine and Compressor Cascade Aerodynamics and Heat Transfer Experimental study of the wake effect on unsteady boundary layer flow and heat transfer of low pressure turbine (LPT) blade Experimental study of the wake effect on unsteady boundary layer flow and heat transfer of high pressure turbine (HPT)blade |
3. Gas turbine Engine Nonlinear Dynamic Simulation Capabilities Code: G E T R A N© : a Generic Modular Structured Non-Linear Computer Code for the Simulation of Dynamic Behavior of Single- and Multi- Spool High Pressure Core Engines, Turbofan Engines and Power Generation Gas Turbine Engines |