Gasroad has participated in the development of auxiliary power units (APUs) for KHP,
acquiring fuel supply and processing technology for the Surion helicopter
and unique technical expertise through the development and patent registration of nozzle injector
cleaning technology. In addition, the company developed and produced small
gas turbine combustors, which are major components of the gas turbine engines used
to drive the main power generators for the Biho complex system, including the 30mm
self-propelled anti-aircraft gun (K30) and the complex anti-aircraft weapon system (K-30 SAM).
- APU Combustor TEST RIG
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- Producing test rig for performance testing of the combustor installed in the APU gas turbine engine
- Test rig that generates combustion gas at 1300K by supplying heated combustion air at 600K and 5.5 bar(a) to the combustor, and injecting fuel (aviation fuel) into the combustor through a fuel manifold and injectors
| Composition |
| Producing APU combustor performance testing rig including the main body, cooling water and cooling air supply systems, fuel supply system and support / Various fasteners |
| Operating conditions |
| TotalInletPressure |
521300 Pa |
| TotalInletTemperature |
550K |
| AirMassFlow |
1.71 kg/sec |
| FuelFlow |
115.2 kg/hr |
| FuelType |
JP-8(항공유) |
| Exhaust Temperature |
1200 K |
- Combustor for gas turbine engine powering the Biho and Biho complex PPU
-
- The centrifugal compressor draws in outside air to propel rotational motion and converts kinetic energy into pressure energy through a diffuser
- The high-temperature, high-pressure gas generated in the combustion chamber is caused to change its flow direction to an appropriate angle by the guide vanes of the nozzle. As it passes through the vanes of the turbine nozzle, it generates centrifugal pressure energy, which causes the turbine to rotate
| Combustor assembly configuration |
| Cumbustor casing, combustor liner, injector nozzle assembly, fuel manifold, temperature sensor assembly, igniter, check valve assembly |
| Spec |
| Size |
Ø296 X 275 mm |
| Weight |
7.0kg |
| Fuel consumption level |
No-load: 36ℓ/h / Full-load: 58ℓ/h |
| Exhaust temperature |
615Ċ |
- Producing fuel supply system for a supersonic regenerative cooling combustor
- Supersonic regenerative cooling combustor and fuel supply system for heat exchanger performance testing
| Component items |
| fuel supply system |
| Operating conditions |
| Maximum operating pressure |
100Mpa |
| Maximum flow rate |
40g/s(JP-8) |
| Electrical specifications |
380V, 3P |
| Flow rate inverter control |
- Producing fuel supply system for testing supersonic combustor
- Producing fuel supply system for performance testing of supersonic combustor
| Component items |
| Fuel supply system |
| Operating conditions |
| Fuel |
Aviation fuel |
| Flow rate |
40g/s |
| Electrical specifications |
380V, 3P |
| Flow rate control unit |
0.075g/s |
| Pressure |
100 barA |
| Fuel tank |
100L |
Gasroad is a technology-intensive company that not only produces combustion testing facilities
and combustors (engines) and develops and produces high-altitude environment test facilities,
but also performs continuous technology development to stabilize and
improve the performance of existing facilities. The company has the capability
to develop optimal testing facilities for accurate and safe experiments
and verifications through optimizing the test conditions in extreme environments.
- BSTF(Designing, producing and installing turbo pump bearing and seal performance testing facilities)
- Performance testing facility for turbo pump bearings and seals at extremely low temperatures
| Cryogenic Control, LO2, LN2 |
| Fuel |
JP-8 |
| OP(Pressure) |
10bar |
| OT(Temperature) |
-55~60℃ |
| FR(Flow rate) |
1,000kg/hr |
| Tank volume |
2,000 LITER |
| Cooling method |
Indirect cooling method using LN2 |
| Flow rate measurement |
Mass & turbine flow meters |
- Fuel Supply System for Engine Testing
- The engine-testing facility is multi-purpose testing equipment, performing free-jet tests which simulate the altitude and speed of an operating engine. Gasroad designs, produces, and installs support systems (LNG supply system, nitrogen supply system, air supply system) among the engine testing facilities
| LNG supply system |
| LNG |
70ton |
| OP |
70bar |
| OT |
-163℃ |
| FR |
10,500m3/hr |
| Cooling method |
Indirect cooling method using LN2 |
| flow rate measurement |
Mass & turbine flow meters |
| H-FUEL Batch Tank, Sub Tank |
| Fuel |
JP-8 / JP-xx |
| OP |
3~82bar |
| OT |
-32~227℃ |
| FR |
20,000kg/hr |
H-FUEL 배치탱크
H-FUEL 서브탱크
- Constructing main piping system for turbine cascade test rig
- Constructing main piping system for test rig flow supply and exhaust for turbine cascade testing (high flow rate main flow supply system) - Design/production, construction, inspection and commissioning
| Business Scope |
Constructing inlet piping system, exhaust piping system and various signal transduction fields, and integrated them with existing measurement systems |
| Spec |
| Inlet pressure / Temperature |
Up to 3 bar / Above 200°C |
| Mass flow rate |
Up to 6kg/s |
| Flow velocity |
Maximum Mach number at the cascade outlet of the test section (exhaust upstream): 1.2 |
- Producing and installing piping for small centrifugal compressor testing facility
-
- Constructing piping for testing facility that enables designing, producing and performance testing of centrifugal compressor, a core component of the multi-stage turbocharger with high-pressure ratio for aviation
- Turbocharger is a device that increases the power output efficiency of an engine relative to its size by using discarded exhaust gas to spin a turbine at high speed. This rotational force drives the centrifugal compressor, which sends compressed air into the engine
- Performance testing facility for centrifugal compressor for a turbocharger, intended for the hydrogen reciprocating engine system operating at high altitude conditions above 18km (~0.05 atm, -56 ℃)
| 제작범위 |
Inlet and outlet piping system (including venturi tube and collector), pressure control valve, pressure gauge, drive unit |
| Test Facility Requirements |
| Inlet pressure |
Minimum 0.25 bar or less |
| Outlet pressure |
Maximum 10 bar or more |
| Inlet temperature |
Minimum -15°C or lower |
| Outlet temperature |
Maximum 400°C or more |
| Flow rate |
Around 1.5 kg/s |
| Inlet pipe flow velocity |
Maximum 30m/s or less upon depressurization by 0.5bar @Settling Chamber |
| Outlet pipe flow velocity |
30-40m/s or less @ Collector outlet branch pipe |
- Scramijet Engine Test Facility
-
- Supersonic ground propulsion testing facility is designed to test a propulsion system operating in the supersonic range and consists of high-pressure air supply, storage-type heating system, engine tester and air ejector system
- The engine test section is an important component equipped with a test model engine, supplies the engine's operating conditions and processes engine exhaust gas
| Engine test section components |
Low pressure chamber, diffuser, Mach number nozzle, engine mount and thrust measuring stand inside the low pressure chamber, sensor panel |
- Producing test chamber and ejector
- Designing, producing and fully installing test chamber and ejector as semi-free-flow test facilities for observing the flow and combustion phenomena of high-speed aircraft (engines) exposed to ultra-high-speed flow environments
| Components |
| Test chamber |
Low-pressure chamber, test object mount and thrust measuring stand, low pressure chamber internal connecting piping, test chamber transport device, flow simulation nozzle support |
| Ejector |
Ejector nozzle, water spray, diffuser assembly |
Gasroad develops efficient testing facilities and equipment suited to specific testing purposes,
based on high-level expertise and experience in manufacturing high-temperature fuel processing equipment,
temperature measurement technology and thermocouple (TC) processing technology
- Producing endothermic fuel channel cooling device
- To study the applicability of endothermic fuels for hypersonic flying vehicles, a multi-channel cooling device is manufactured to conduct a prescribed cooling test by creating a cooling channel test model with heat-resistant composites and high-strength heat-resistant metal materials, and testing the endothermic reaction in a designated high-temperature/high-pressure environment
| Equipment components |
| Fuel supply unit, heater control unit, endothermic reaction test section, fuel recovery unit, control and measurement unit, test safety unit, heat-resistant composite endothermic reactor model, metal endothermic decomposition catalyst reactor model |
| Operating conditions |
| Heating the wall of the endothermic reactor to a constant 1500K |
| Fuel supply mass flow rate 6-70 g/s @ 50 bar, temperatures 400, 600 and 700K |
| 2 types of fuel used (n-dodecane, JP-*) |
| Exhaust fuel sample |
gas and liquid collection in each test |
| Maximum operating pressure |
50Bar |
- Producing simulation testing device for high-temperature engine
- Engine simulator capable of generating a 700℃ plume and stably fixing and rotating the exhaust outlet
| Production scope |
| Exhaust gas simulation technology (Combustor manufacturing technology) |
| Combustion flow rate control technology |
| Hydraulic and pneumatic control technology |
| Exhaust gas flow rate |
| Given flow velocity |
1m/s |
| Nozzle inlet diameter |
530mm(0.53m) |
| Exhaust gas temperature |
700℃ |
| Exhaust gas flow rate from Q=AV is 0.22m3/s |
