TURBOEXP performs experimentation and testing activities for gas turbine engines as turboshafts, turbojets, microturbojets and various technical demonstrators that involved different types of gas turbine engines. The TURBOEXP experimental research infrastructure is unique in Romania, and it has a technological and performance level according to international standards (SAE).
TURBOEXP main function is scientific research by testing and experimentation
TURBOEXP hold experimentation and testing facilities for:
- Aviation gas turbine engines in service and out of service
- Gas Turbine Engines equipped with electronic control units (ECU, DEEC, FADEC)
- Aeroderivative, marine and industrial gas turbine engines
- Gas turbine engines conversions
- Gas turbine engines technical demonstrators (marine propulsion system, cogeneration, power generation)
Globally, TURBOEXP contains:
- 1 Test Cell for turboshaft and turboprop engines with maximum shaft power of 5200 kW
- 1 Test Cell for turbojets and turbofan engines with maximum thrust of 10000 kgf
- 1 Microjet Test Bench with maximum thrust of 250 kgf
- Data Acquisition Control System (DACS) from SAFRAN Cenco International
- Mobile Acquisition Cabinet (MAC) from SAFRAN Cenco International
- Command and Control Room (COMOTI & SAFRAN Cenco International)
- Additional data Acquisition Unit made by COMOTI
- Fuel, oil, pneumatic, water and electrical auxiliary installations
The turboshaft and turboprop test Cell with maximum shaft power of 5200 kW assure testing facilities for different types of engines as:
- Turboshaft engines with free power turbine
- Turboshaft engines without free power turbine
- Turboshaft engines with constant speed law of free power turbine
- Turboshaft engines with variable speed law of free power turbine
- Turboshaft engines with constant speed law of shaft power (for engines without free power turbine)
- Turboshaft engines with front shaft power
- Turboshaft engines with rear shaft power
The turboshaft and turboprop test cell allows the engines to be operated in manual or auto mode, in function of shaft speed setting, in function of shaft torque setting and in function of speed and torque working curve or law.
The turboshaft and turboprop Test Cell contains:
- Shaft power measuring System (Two Froude Hofmann HS2600 Hydraulic Dynamometer, Power: 2 x 2600 kW, Shaft Speed: 24000 rpm, Torque: 2 x 1356 Nm)
- Electrical power sourse for electrical starters (RDTP 48V/1000A Electrotehnica)
- Instrumentation system for engine and auxiliary instalations (DO, AO, DI, Speed, Vibrations, Flows, Pressures, Temperatures)
- Additional digital Acquisition Unit made by COMOTI
- Air dry pneumatic instalations of 12 bar nominal pressure for pneumatic starters and other auxilary air utilities
- CO2 fire detection, alarm and control system (Industrial Cruman)
Turboshaft and turboprop test Cell
Froude Hofmann HS2600 Hydraulic Dynamometers, Technical Specifications: Power: 5200 kW, Shaft Speed: 24000 rpm, Torque: 2712 Nm
TEST PORTFOLIO
Testing of TV2-117A free turbine turboshaft, Engine Manufacturer: KLIMOV, Technical Specification: Power: 1100 kW, Free turbine speed: 12000 rpm, Gasgenerator speed: 21200 rpm, Specific fuel consumption: 0.257 kg/HP/h, Application: MI-8.
Testing of TV3-117MT free turbine turboshaft: Engine Manufacturer: KLIMOV, Technical Specification: Power: 1600 kW, Free turbine speed: 15000 rpm, Gasgenerator speed: 19500 rpm, Specific fuel consumption 0.230 kg/HP/h, Application: MI-17.
Testing of SOLAR free turbine. Turbine manufacturer: Comoti, Technical Specification: Power: 3500 HP, Turbine speed: 11000 rpm. The testing was performed by using gases flow from two gasgenerators of free turbine turboshaft TV2-117A. Customer: TRANSGAS Romania
Testing of R11-F300 birotor jet engine, Engine Manufacturer: Tumansky, Technical Specification: Thrust 3900 kgf, LP shaft speed: 11425 rpm, HP shaft speed: 11150 rpm, Air mass flow: 65.7 kg/s, Specific fuel consumption: 0.96 kg/kgf/h, Application: MIG-21
Testing of MTI-1500 Stage-III experimental free turbine using the gasgenerator of the free turbine turboshaft TV2-117A, Technical Specification: Maximum Speed: 22000 rpm, Maximum Speed of testing: 16000 rpm, Inlet turbine maximum temperature: 450 °C, Turbine manufacturing material: X19CrMoNbVN11-1 (1.4913)
Testing configuration of the MTI1-1500 Stage III experimental free turbine.
MTI-1500 Stage-III experimental free turbine on the test bench
Project: TURBONAV 34SOL/2021 ”Marine Propulsion Group (GPN) T22-ST40M” & TURBONAV A5-1373, Testing of ST40M free turbine turboshaft, Engine Manufacturer: Pratt & Whitney, Project Manufacturer: COMOTI, Technical Specification: Power: 4167 kW, free turbine speed: 16000 rpm, gasgenerator HP shaft speed: 31150 rpm, Fuel consumption: 1200 kg/h.
GPN NPRM-ST40M Marine Propulsion Group Technical Demonstrator on the test bench
Project: NAVIPROM 34SOL/2021 Marine Propulsion Group ”GPN NPRM-ST40M”, Testing of ST40M free turbine turboshaft, Engine Manufacturer: Pratt & Whitney, Project Manufacturer: COMOTI, Technical Specification: Power: 4167 kW, free turbine speed: 16000 rpm, gasgenerator HP shaft speed: 31150 rpm, Fuel consumption 1200 kg/h.
CAD draw with installation scheme of technical demonstrator: ”GPN NPRM-ST40M”
Marine Propulsion Group GPN NPRM-ST40M technical demonstrator on the test bench
Data Acquisition Control System (DACS), System Manufacturer: SAFRAN Cenco International
Data Acquisition Control System (DACS) is a configurable and adaptable system consisting of a hardware component which includes a mobile data acquisition cabinet (MAC) and an operating module component with a programmable software (Cyres V8). DACS allows to be configurable for every particular test application and allows the control and real time monitoring for various gas turbine engines models
Data Acquisition Control System (DACS), works with hundreds of parameters, with an acquisition rate up to 10 kHz, with the capacity of communication with various PLCs (programmable logic controller) and various acquisition modules, with data transfer protocol via Ethernet. Mobile Acquisition Cabinet (MAC) contains GANTNER acquisition modules consisting of a minimum 128 measurement channels.
Technical Arhitecture of Data Acquisition Control System DACS
Additional data Acquisition Unit made by COMOTI
TURBOEXP holds a command and control room who servses both test cell, turboshaft and turbojets. Through the DACS operating system, from the control room the engines it is assure the controlling of engines and real time engines monitoring using a specific Graphical User Interface.
Command and control room
Graphical User Interface for Testing of TV2-117A free turbine turboshaft
Graphical User Interface for Testing of TV3-117MT free turbine turboshaft
Graphical User Interface for Testing of R11-F300 birotor jet engine
Graphical User Interface for ST40M free turbine turboshaft
Graphical User Interface of the TEXCEL VX100 Dynamometer Operator System
