RESEARCH NEWSLETTER OCT. '98
List of Archival Publications
ARCHIVAL PUBLICATIONS
FACILITIES:-
Three large, reinforced concrete buildings of special design and one
metal building (machine shop), located on the edge of the Monterey Peninsula
Airport within the Naval Postgraduate School Golf Course enclosure.
Low Speed Turbopropulsion Laboratory (Bldg. 213)
For low speed experiments; contains a 700 HP blower in the basement,
external inlet and exhaust towers, electrically actuated windows on all sides,
pressure and suction floor panels, and is equipped with a 6000 lb. capacity
overhead travelling hoist. A unique facility, the laboratory houses three
major rigs and data systems as follows:
RECTILINEAR CASCADE WIND TUNNEL
- Test Section 10" by 60"
- Turning Angle 0 - 160 deg.
- Mach No. 0 - 0.4
- Fully automated 2-D LDV system
- Semi-automatic probe traverses
3-STAGE AXIAL COMPRESSOR
- Outer Diameter 36"
- Hub - Tip Ratio 0.6
- Power 150 HP
- Speed 1.2, 1.6 & 2.4 KRPM
- Fully Instrumented
CENTRIFUGAL DIFFUSER TEST DEVICE
- Test Section 50" - 96" Diam. by 2"
- Mach No. 0 - 0.3
- Flow Angle 58 deg. to 72 deg.
- Survey Probes and LDV Access
DATA ACQUISITION SYSTEMS
- HP3052A Data Acquisition System
- Pneumatic Scanivalves (5x48)
- Temp. RPM, Torque, Kullites
- HP9000 Series 300 Computer
- TSI Two-Component LDV System, Standard Optics, XYZ Traverse Table
- TSI Four Channel Hot Wire System
High Speed Turbopropulsion Laboratory (Bldg. 215)
Reinforced concrete building containing a 1200 HP compressed-air power
supply (11 lbs/sec at 3 atmospheres, continuous), two explosion-proof test
cells for high speed compressor and turbine testing, calibration and model
test bay, control room, computer room, conference room and offices. The two
major rigs and data systems are as follows:
TURBINE TEST RIG
- Power 0 - 250 HP (Air and Water Dynamometers)
- Speed 0 - 20,000 RPM
- Diameter 10" approx.
- Turbines:
- Impulse (140 deg. Rotor)
- Space Shuttle Main Engine, High Pressure Fuel Turbopump
- Two Reaction Turbines
- Instrumented for torque, RPM, pressures, temperatures and LDV access.
COMPRESSOR TEST RIG
- Power 0 - 450 HP (Air Turbine Driven)
- Speed 0 - 31,000 RPM
- Diameter 11" approx.
- Compressors:
- Hybrid (Radial-Axial in Rotor)
- Transonic Fan Stage, H. Vavra Design
- Transonic Single Stage, N. Sanger CFD Design (NASA)
- Transonic Single Stage, N. Sanger CFD Design (NASA) Rotor and Transparent Casing
- Instrumented for torque, RPM, pressures, Kullite probes, temperatures and LDV access.
CALIBRATION AND MODEL TEST BAY
- Turbocharger Test Rig
- Calibration Free Jet (7" & 4.25")
- Wave Rotor Apparatus
- Annular Turbine Cascade
- Turbine Nozzle
- Instrumented for LDV Access
HOT SPIN-PIT TEST FACILITY
ARCHIVAL PUBLICATIONS
FACILITIES:-
Three large, reinforced concrete buildings of special design and one
metal building (machine shop), located on the edge of the Monterey Peninsula
Airport within the Naval Postgraduate School Golf Course enclosure.
Low Speed Turbopropulsion Laboratory (Bldg. 213)
For low speed experiments; contains a 700 HP blower in the basement,
external inlet and exhaust towers, electrically actuated windows on all sides,
pressure and suction floor panels, and is equipped with a 6000 lb. capacity
overhead travelling hoist. A unique facility, the laboratory houses three
major rigs and data systems as follows:
RECTILINEAR CASCADE WIND TUNNEL
- Test Section 10" by 60"
- Turning Angle 0 - 160 deg.
- Mach No. 0 - 0.4
- Fully automated 2-D LDV system
- Semi-automatic probe traverses
3-STAGE AXIAL COMPRESSOR
- Outer Diameter 36"
- Hub - Tip Ratio 0.6
- Power 150 HP
- Speed 1.2, 1.6 & 2.4 KRPM
- Fully Instrumented
CENTRIFUGAL DIFFUSER TEST DEVICE
- Test Section 50" - 96" Diam. by 2"
- Mach No. 0 - 0.3
- Flow Angle 58 deg. to 72 deg.
- Survey Probes and LDV Access
DATA ACQUISITION SYSTEMS
- HP3052A Data Acquisition System
- Pneumatic Scanivalves (5x48)
- Temp. RPM, Torque, Kullites
- HP9000 Series 300 Computer
- TSI Two-Component LDV System, Standard Optics, XYZ Traverse Table
- TSI Four Channel Hot Wire System
High Speed Turbopropulsion Laboratory (Bldg. 215)
Reinforced concrete building containing a 1200 HP compressed-air power
supply (11 lbs/sec at 3 atmospheres, continuous), two explosion-proof test
cells for high speed compressor and turbine testing, calibration and model
test bay, control room, computer room, conference room and offices. The two
major rigs and data systems are as follows:
TURBINE TEST RIG
- Power 0 - 250 HP (Air and Water Dynamometers)
- Speed 0 - 20,000 RPM
- Diameter 10" approx.
- Turbines:
- Impulse (140 deg. Rotor)
- Space Shuttle Main Engine, High Pressure Fuel Turbopump
- Two Reaction Turbines
- Instrumented for torque, RPM, pressures, temperatures and LDV access.
COMPRESSOR TEST RIG
- Power 0 - 450 HP (Air Turbine Driven)
- Speed 0 - 31,000 RPM
- Diameter 11" approx.
- Compressors:
- Hybrid (Radial-Axial in Rotor)
- Transonic Fan Stage, H. Vavra Design
- Transonic Single Stage, N. Sanger CFD Design (NASA)
- Transonic Single Stage, N. Sanger CFD Design (NASA) Rotor and Transparent Casing
- Instrumented for torque, RPM, pressures, Kullite probes, temperatures and LDV access.
CALIBRATION AND MODEL TEST BAY
- Turbocharger Test Rig
- Calibration Free Jet (7" & 4.25")
- Wave Rotor Apparatus
- Annular Turbine Cascade
- Turbine Nozzle
- Instrumented for LDV Access
HOT SPIN-PIT TEST FACILITY
Three large, reinforced concrete buildings of special design and one
metal building (machine shop), located on the edge of the Monterey Peninsula
Airport within the Naval Postgraduate School Golf Course enclosure.
Low Speed Turbopropulsion Laboratory (Bldg. 213)
For low speed experiments; contains a 700 HP blower in the basement,
external inlet and exhaust towers, electrically actuated windows on all sides,
pressure and suction floor panels, and is equipped with a 6000 lb. capacity
overhead travelling hoist. A unique facility, the laboratory houses three
major rigs and data systems as follows:
RECTILINEAR CASCADE WIND TUNNEL
- Test Section 10" by 60"
- Turning Angle 0 - 160 deg.
- Mach No. 0 - 0.4
- Fully automated 2-D LDV system
- Semi-automatic probe traverses
3-STAGE AXIAL COMPRESSOR
- Outer Diameter 36"
- Hub - Tip Ratio 0.6
- Power 150 HP
- Speed 1.2, 1.6 & 2.4 KRPM
- Fully Instrumented
CENTRIFUGAL DIFFUSER TEST DEVICE
- Test Section 50" - 96" Diam. by 2"
- Mach No. 0 - 0.3
- Flow Angle 58 deg. to 72 deg.
- Survey Probes and LDV Access
DATA ACQUISITION SYSTEMS
- HP3052A Data Acquisition System
- Pneumatic Scanivalves (5x48)
- Temp. RPM, Torque, Kullites
- HP9000 Series 300 Computer
- TSI Two-Component LDV System, Standard Optics, XYZ Traverse Table
- TSI Four Channel Hot Wire System
High Speed Turbopropulsion Laboratory (Bldg. 215)
Reinforced concrete building containing a 1200 HP compressed-air power
supply (11 lbs/sec at 3 atmospheres, continuous), two explosion-proof test
cells for high speed compressor and turbine testing, calibration and model
test bay, control room, computer room, conference room and offices. The two
major rigs and data systems are as follows:
TURBINE TEST RIG
- Power 0 - 250 HP (Air and Water Dynamometers)
- Speed 0 - 20,000 RPM
- Diameter 10" approx.
- Turbines:
- Impulse (140 deg. Rotor)
- Space Shuttle Main Engine, High Pressure Fuel Turbopump
- Two Reaction Turbines
- Instrumented for torque, RPM, pressures, temperatures and LDV access.
COMPRESSOR TEST RIG
- Power 0 - 450 HP (Air Turbine Driven)
- Speed 0 - 31,000 RPM
- Diameter 11" approx.
- Compressors:
- Hybrid (Radial-Axial in Rotor)
- Transonic Fan Stage, H. Vavra Design
- Transonic Single Stage, N. Sanger CFD Design (NASA)
- Transonic Single Stage, N. Sanger CFD Design (NASA) Rotor and Transparent Casing
- Instrumented for torque, RPM, pressures, Kullite probes, temperatures and LDV access.
CALIBRATION AND MODEL TEST BAY
- Turbocharger Test Rig
- Calibration Free Jet (7" & 4.25")
- Wave Rotor Apparatus
- Annular Turbine Cascade
- Turbine Nozzle
- Instrumented for LDV Access
HOT SPIN-PIT TEST FACILITY
Low Speed Turbopropulsion Laboratory (Bldg. 213)
For low speed experiments; contains a 700 HP blower in the basement,
external inlet and exhaust towers, electrically actuated windows on all sides,
pressure and suction floor panels, and is equipped with a 6000 lb. capacity
overhead travelling hoist. A unique facility, the laboratory houses three
major rigs and data systems as follows:
RECTILINEAR CASCADE WIND TUNNEL
- Test Section 10" by 60"
- Turning Angle 0 - 160 deg.
- Mach No. 0 - 0.4
- Fully automated 2-D LDV system
- Semi-automatic probe traverses
3-STAGE AXIAL COMPRESSOR
- Outer Diameter 36"
- Hub - Tip Ratio 0.6
- Power 150 HP
- Speed 1.2, 1.6 & 2.4 KRPM
- Fully Instrumented
CENTRIFUGAL DIFFUSER TEST DEVICE
- Test Section 50" - 96" Diam. by 2"
- Mach No. 0 - 0.3
- Flow Angle 58 deg. to 72 deg.
- Survey Probes and LDV Access
DATA ACQUISITION SYSTEMS
- HP3052A Data Acquisition System
- Pneumatic Scanivalves (5x48)
- Temp. RPM, Torque, Kullites
- HP9000 Series 300 Computer
- TSI Two-Component LDV System, Standard Optics, XYZ Traverse Table
- TSI Four Channel Hot Wire System
High Speed Turbopropulsion Laboratory (Bldg. 215)
Reinforced concrete building containing a 1200 HP compressed-air power
supply (11 lbs/sec at 3 atmospheres, continuous), two explosion-proof test
cells for high speed compressor and turbine testing, calibration and model
test bay, control room, computer room, conference room and offices. The two
major rigs and data systems are as follows:
TURBINE TEST RIG
- Power 0 - 250 HP (Air and Water Dynamometers)
- Speed 0 - 20,000 RPM
- Diameter 10" approx.
- Turbines:
- Impulse (140 deg. Rotor)
- Space Shuttle Main Engine, High Pressure Fuel Turbopump
- Two Reaction Turbines
- Instrumented for torque, RPM, pressures, temperatures and LDV access.
COMPRESSOR TEST RIG
- Power 0 - 450 HP (Air Turbine Driven)
- Speed 0 - 31,000 RPM
- Diameter 11" approx.
- Compressors:
- Hybrid (Radial-Axial in Rotor)
- Transonic Fan Stage, H. Vavra Design
- Transonic Single Stage, N. Sanger CFD Design (NASA)
- Transonic Single Stage, N. Sanger CFD Design (NASA) Rotor and Transparent Casing
- Instrumented for torque, RPM, pressures, Kullite probes, temperatures and LDV access.
CALIBRATION AND MODEL TEST BAY
- Turbocharger Test Rig
- Calibration Free Jet (7" & 4.25")
- Wave Rotor Apparatus
- Annular Turbine Cascade
- Turbine Nozzle
- Instrumented for LDV Access
HOT SPIN-PIT TEST FACILITY
Low Speed Turbopropulsion Laboratory (Bldg. 213)
RECTILINEAR CASCADE WIND TUNNEL
- Test Section 10" by 60"
- Turning Angle 0 - 160 deg.
- Mach No. 0 - 0.4
- Fully automated 2-D LDV system
- Semi-automatic probe traverses
3-STAGE AXIAL COMPRESSOR
- Outer Diameter 36"
- Hub - Tip Ratio 0.6
- Power 150 HP
- Speed 1.2, 1.6 & 2.4 KRPM
- Fully Instrumented
CENTRIFUGAL DIFFUSER TEST DEVICE
- Test Section 50" - 96" Diam. by 2"
- Mach No. 0 - 0.3
- Flow Angle 58 deg. to 72 deg.
- Survey Probes and LDV Access
DATA ACQUISITION SYSTEMS
- HP3052A Data Acquisition System
- Pneumatic Scanivalves (5x48)
- Temp. RPM, Torque, Kullites
- HP9000 Series 300 Computer
- TSI Two-Component LDV System, Standard Optics, XYZ Traverse Table
- TSI Four Channel Hot Wire System
High Speed Turbopropulsion Laboratory (Bldg. 215)
Reinforced concrete building containing a 1200 HP compressed-air power
supply (11 lbs/sec at 3 atmospheres, continuous), two explosion-proof test
cells for high speed compressor and turbine testing, calibration and model
test bay, control room, computer room, conference room and offices. The two
major rigs and data systems are as follows:
TURBINE TEST RIG
- Power 0 - 250 HP (Air and Water Dynamometers)
- Speed 0 - 20,000 RPM
- Diameter 10" approx.
- Turbines:
- Impulse (140 deg. Rotor)
- Space Shuttle Main Engine, High Pressure Fuel Turbopump
- Two Reaction Turbines
- Instrumented for torque, RPM, pressures, temperatures and LDV access.
COMPRESSOR TEST RIG
- Power 0 - 450 HP (Air Turbine Driven)
- Speed 0 - 31,000 RPM
- Diameter 11" approx.
- Compressors:
- Hybrid (Radial-Axial in Rotor)
- Transonic Fan Stage, H. Vavra Design
- Transonic Single Stage, N. Sanger CFD Design (NASA)
- Transonic Single Stage, N. Sanger CFD Design (NASA) Rotor and Transparent Casing
- Instrumented for torque, RPM, pressures, Kullite probes, temperatures and LDV access.
CALIBRATION AND MODEL TEST BAY
- Turbocharger Test Rig
- Calibration Free Jet (7" & 4.25")
- Wave Rotor Apparatus
- Annular Turbine Cascade
- Turbine Nozzle
- Instrumented for LDV Access
HOT SPIN-PIT TEST FACILITY
- Test Section 10" by 60"
- Turning Angle 0 - 160 deg.
- Mach No. 0 - 0.4
- Fully automated 2-D LDV system
- Semi-automatic probe traverses
3-STAGE AXIAL COMPRESSOR
- Outer Diameter 36"
- Hub - Tip Ratio 0.6
- Power 150 HP
- Speed 1.2, 1.6 & 2.4 KRPM
- Fully Instrumented
CENTRIFUGAL DIFFUSER TEST DEVICE
- Test Section 50" - 96" Diam. by 2"
- Mach No. 0 - 0.3
- Flow Angle 58 deg. to 72 deg.
- Survey Probes and LDV Access
DATA ACQUISITION SYSTEMS
- HP3052A Data Acquisition System
- Pneumatic Scanivalves (5x48)
- Temp. RPM, Torque, Kullites
- HP9000 Series 300 Computer
- TSI Two-Component LDV System, Standard Optics, XYZ Traverse Table
- TSI Four Channel Hot Wire System
High Speed Turbopropulsion Laboratory (Bldg. 215)
Reinforced concrete building containing a 1200 HP compressed-air power
supply (11 lbs/sec at 3 atmospheres, continuous), two explosion-proof test
cells for high speed compressor and turbine testing, calibration and model
test bay, control room, computer room, conference room and offices. The two
major rigs and data systems are as follows:
TURBINE TEST RIG
- Power 0 - 250 HP (Air and Water Dynamometers)
- Speed 0 - 20,000 RPM
- Diameter 10" approx.
- Turbines:
- Impulse (140 deg. Rotor)
- Space Shuttle Main Engine, High Pressure Fuel Turbopump
- Two Reaction Turbines
- Instrumented for torque, RPM, pressures, temperatures and LDV access.
COMPRESSOR TEST RIG
- Power 0 - 450 HP (Air Turbine Driven)
- Speed 0 - 31,000 RPM
- Diameter 11" approx.
- Compressors:
- Hybrid (Radial-Axial in Rotor)
- Transonic Fan Stage, H. Vavra Design
- Transonic Single Stage, N. Sanger CFD Design (NASA)
- Transonic Single Stage, N. Sanger CFD Design (NASA) Rotor and Transparent Casing
- Instrumented for torque, RPM, pressures, Kullite probes, temperatures and LDV access.
CALIBRATION AND MODEL TEST BAY
- Turbocharger Test Rig
- Calibration Free Jet (7" & 4.25")
- Wave Rotor Apparatus
- Annular Turbine Cascade
- Turbine Nozzle
- Instrumented for LDV Access
HOT SPIN-PIT TEST FACILITY
- Outer Diameter 36"
- Hub - Tip Ratio 0.6
- Power 150 HP
- Speed 1.2, 1.6 & 2.4 KRPM
- Fully Instrumented
CENTRIFUGAL DIFFUSER TEST DEVICE
- Test Section 50" - 96" Diam. by 2"
- Mach No. 0 - 0.3
- Flow Angle 58 deg. to 72 deg.
- Survey Probes and LDV Access
DATA ACQUISITION SYSTEMS
- HP3052A Data Acquisition System
- Pneumatic Scanivalves (5x48)
- Temp. RPM, Torque, Kullites
- HP9000 Series 300 Computer
- TSI Two-Component LDV System, Standard Optics, XYZ Traverse Table
- TSI Four Channel Hot Wire System
High Speed Turbopropulsion Laboratory (Bldg. 215)
Reinforced concrete building containing a 1200 HP compressed-air power
supply (11 lbs/sec at 3 atmospheres, continuous), two explosion-proof test
cells for high speed compressor and turbine testing, calibration and model
test bay, control room, computer room, conference room and offices. The two
major rigs and data systems are as follows:
TURBINE TEST RIG
- Power 0 - 250 HP (Air and Water Dynamometers)
- Speed 0 - 20,000 RPM
- Diameter 10" approx.
- Turbines:
- Impulse (140 deg. Rotor)
- Space Shuttle Main Engine, High Pressure Fuel Turbopump
- Two Reaction Turbines
- Instrumented for torque, RPM, pressures, temperatures and LDV access.
COMPRESSOR TEST RIG
- Power 0 - 450 HP (Air Turbine Driven)
- Speed 0 - 31,000 RPM
- Diameter 11" approx.
- Compressors:
- Hybrid (Radial-Axial in Rotor)
- Transonic Fan Stage, H. Vavra Design
- Transonic Single Stage, N. Sanger CFD Design (NASA)
- Transonic Single Stage, N. Sanger CFD Design (NASA) Rotor and Transparent Casing
- Instrumented for torque, RPM, pressures, Kullite probes, temperatures and LDV access.
CALIBRATION AND MODEL TEST BAY
- Turbocharger Test Rig
- Calibration Free Jet (7" & 4.25")
- Wave Rotor Apparatus
- Annular Turbine Cascade
- Turbine Nozzle
- Instrumented for LDV Access
HOT SPIN-PIT TEST FACILITY
- Test Section 50" - 96" Diam. by 2"
- Mach No. 0 - 0.3
- Flow Angle 58 deg. to 72 deg.
- Survey Probes and LDV Access
DATA ACQUISITION SYSTEMS
- HP3052A Data Acquisition System
- Pneumatic Scanivalves (5x48)
- Temp. RPM, Torque, Kullites
- HP9000 Series 300 Computer
- TSI Two-Component LDV System, Standard Optics, XYZ Traverse Table
- TSI Four Channel Hot Wire System
High Speed Turbopropulsion Laboratory (Bldg. 215)
Reinforced concrete building containing a 1200 HP compressed-air power
supply (11 lbs/sec at 3 atmospheres, continuous), two explosion-proof test
cells for high speed compressor and turbine testing, calibration and model
test bay, control room, computer room, conference room and offices. The two
major rigs and data systems are as follows:
TURBINE TEST RIG
- Power 0 - 250 HP (Air and Water Dynamometers)
- Speed 0 - 20,000 RPM
- Diameter 10" approx.
- Turbines:
- Impulse (140 deg. Rotor)
- Space Shuttle Main Engine, High Pressure Fuel Turbopump
- Two Reaction Turbines
- Instrumented for torque, RPM, pressures, temperatures and LDV access.
COMPRESSOR TEST RIG
- Power 0 - 450 HP (Air Turbine Driven)
- Speed 0 - 31,000 RPM
- Diameter 11" approx.
- Compressors:
- Hybrid (Radial-Axial in Rotor)
- Transonic Fan Stage, H. Vavra Design
- Transonic Single Stage, N. Sanger CFD Design (NASA)
- Transonic Single Stage, N. Sanger CFD Design (NASA) Rotor and Transparent Casing
- Instrumented for torque, RPM, pressures, Kullite probes, temperatures and LDV access.
CALIBRATION AND MODEL TEST BAY
- Turbocharger Test Rig
- Calibration Free Jet (7" & 4.25")
- Wave Rotor Apparatus
- Annular Turbine Cascade
- Turbine Nozzle
- Instrumented for LDV Access
HOT SPIN-PIT TEST FACILITY
- HP3052A Data Acquisition System
- Pneumatic Scanivalves (5x48)
- Temp. RPM, Torque, Kullites
- HP9000 Series 300 Computer
- TSI Two-Component LDV System, Standard Optics, XYZ Traverse Table
- TSI Four Channel Hot Wire System
High Speed Turbopropulsion Laboratory (Bldg. 215)
Reinforced concrete building containing a 1200 HP compressed-air power
supply (11 lbs/sec at 3 atmospheres, continuous), two explosion-proof test
cells for high speed compressor and turbine testing, calibration and model
test bay, control room, computer room, conference room and offices. The two
major rigs and data systems are as follows:
TURBINE TEST RIG
- Power 0 - 250 HP (Air and Water Dynamometers)
- Speed 0 - 20,000 RPM
- Diameter 10" approx.
- Turbines:
- Impulse (140 deg. Rotor)
- Space Shuttle Main Engine, High Pressure Fuel Turbopump
- Two Reaction Turbines
- Instrumented for torque, RPM, pressures, temperatures and LDV access.
COMPRESSOR TEST RIG
- Power 0 - 450 HP (Air Turbine Driven)
- Speed 0 - 31,000 RPM
- Diameter 11" approx.
- Compressors:
- Hybrid (Radial-Axial in Rotor)
- Transonic Fan Stage, H. Vavra Design
- Transonic Single Stage, N. Sanger CFD Design (NASA)
- Transonic Single Stage, N. Sanger CFD Design (NASA) Rotor and Transparent Casing
- Instrumented for torque, RPM, pressures, Kullite probes, temperatures and LDV access.
CALIBRATION AND MODEL TEST BAY
- Turbocharger Test Rig
- Calibration Free Jet (7" & 4.25")
- Wave Rotor Apparatus
- Annular Turbine Cascade
- Turbine Nozzle
- Instrumented for LDV Access
HOT SPIN-PIT TEST FACILITY
High Speed Turbopropulsion Laboratory (Bldg. 215)
TURBINE TEST RIG
- Power 0 - 250 HP (Air and Water Dynamometers)
- Speed 0 - 20,000 RPM
- Diameter 10" approx.
- Turbines:
- Impulse (140 deg. Rotor)
- Space Shuttle Main Engine, High Pressure Fuel Turbopump
- Two Reaction Turbines
- Instrumented for torque, RPM, pressures, temperatures and LDV access.
COMPRESSOR TEST RIG
- Power 0 - 450 HP (Air Turbine Driven)
- Speed 0 - 31,000 RPM
- Diameter 11" approx.
- Compressors:
- Hybrid (Radial-Axial in Rotor)
- Transonic Fan Stage, H. Vavra Design
- Transonic Single Stage, N. Sanger CFD Design (NASA)
- Transonic Single Stage, N. Sanger CFD Design (NASA) Rotor and Transparent Casing
- Instrumented for torque, RPM, pressures, Kullite probes, temperatures and LDV access.
CALIBRATION AND MODEL TEST BAY
- Turbocharger Test Rig
- Calibration Free Jet (7" & 4.25")
- Wave Rotor Apparatus
- Annular Turbine Cascade
- Turbine Nozzle
- Instrumented for LDV Access
HOT SPIN-PIT TEST FACILITY
- Power 0 - 250 HP (Air and Water Dynamometers)
- Speed 0 - 20,000 RPM
- Diameter 10" approx.
- Turbines:
- Impulse (140 deg. Rotor)
- Space Shuttle Main Engine, High Pressure Fuel Turbopump
- Two Reaction Turbines
- Instrumented for torque, RPM, pressures, temperatures and LDV access.
COMPRESSOR TEST RIG
- Power 0 - 450 HP (Air Turbine Driven)
- Speed 0 - 31,000 RPM
- Diameter 11" approx.
- Compressors:
- Hybrid (Radial-Axial in Rotor)
- Transonic Fan Stage, H. Vavra Design
- Transonic Single Stage, N. Sanger CFD Design (NASA)
- Transonic Single Stage, N. Sanger CFD Design (NASA) Rotor and Transparent Casing
- Instrumented for torque, RPM, pressures, Kullite probes, temperatures and LDV access.
CALIBRATION AND MODEL TEST BAY
- Turbocharger Test Rig
- Calibration Free Jet (7" & 4.25")
- Wave Rotor Apparatus
- Annular Turbine Cascade
- Turbine Nozzle
- Instrumented for LDV Access
HOT SPIN-PIT TEST FACILITY
- Power 0 - 450 HP (Air Turbine Driven)
- Speed 0 - 31,000 RPM
- Diameter 11" approx.
- Compressors:
- Hybrid (Radial-Axial in Rotor)
- Transonic Fan Stage, H. Vavra Design
- Transonic Single Stage, N. Sanger CFD Design (NASA)
- Transonic Single Stage, N. Sanger CFD Design (NASA) Rotor and Transparent Casing
- Instrumented for torque, RPM, pressures, Kullite probes, temperatures and LDV access.
CALIBRATION AND MODEL TEST BAY
- Turbocharger Test Rig
- Calibration Free Jet (7" & 4.25")
- Wave Rotor Apparatus
- Annular Turbine Cascade
- Turbine Nozzle
- Instrumented for LDV Access
HOT SPIN-PIT TEST FACILITY
- Turbocharger Test Rig
- Calibration Free Jet (7" & 4.25")
- Wave Rotor Apparatus
- Annular Turbine Cascade
- Turbine Nozzle
- Instrumented for LDV Access
HOT SPIN-PIT TEST FACILITY
