Turbocharged Gasoline Aero Piston Engine with 300 kW to 1,000 kW Power Range, 2,000-hour TBO Cycle, and 10%-15% Power Drop at 4,000 m
The L/V family represents a comprehensive range of turbocharged gasoline aviation piston engines, featuring inline L-series (3/4/5-cylinder) and V6 series (6-cylinder V-layout) configurations. The power spectrum covers continuous output from 300 kW to 1,000 kW, targeting high-performance manned aerial vehicles. All models utilize aviation gasoline fuel and share a unified 2,000-hour TBO cycle. At 4,000 m altitude, power loss is controlled within 10%-15% under turbo compensation.
| Displacement | 1.6-1.8 L |
| Maximum hardware power capacity | 750 kW |
| Rated take-off power | 300-400 kW |
| Continuous cruising power | 300 kW |
| Operating speed range | 5,500-6,000 rpm |
| Dry mass | 95 kg |
| Power-to-weight ratio | 3.1-4.2 kW/kg |
| Approved fuel | 95# / 98# / 100LL aviation gasoline |
| Specific fuel consumption | 220-310 g/kWh |
| TBO interval | 2,000 flight hours |
| Altitude performance | Only 10%-15% power drop at 4,000 m above sea level |
| Displacement | 2.0-2.4 L |
| Maximum hardware power capacity | 800 kW |
| Rated take-off power | 300-400 kW |
| Continuous cruising power | 300 kW |
| Operating speed range | 5,500-6,500 rpm |
| Dry mass | 125 kg |
| Power-to-weight ratio | 2.4-3.2 kW/kg |
| Approved fuel | 95# / 98# / 100LL aviation gasoline |
| Specific fuel consumption | 220-310 g/kWh |
| TBO interval | 2,000 flight hours |
| Altitude performance | Only 10%-15% power drop at 4,000 m above sea level |
| Displacement | 2.0-2.4 L (same as standard L401) |
| Maximum hardware power capacity | 1,300 kW (turbine & internal reinforcement upgraded) |
| Rated take-off power | 400-500 kW |
| Continuous cruising power | 400 kW |
| Operating speed range | 5,500-8,000 rpm (extended high-rev band) |
| Dry mass | 115 kg (10 kg lighter than standard 4-cylinder model via lightweight casting) |
| Power-to-weight ratio | 3.4-4.3 kW/kg |
| Approved fuel | 95# / 98# / 100LL aviation gasoline |
| Specific fuel consumption | 220-310 g/kWh |
| TBO interval | 2,000 flight hours |
| Altitude performance | Only 10%-15% power drop at 4,000 m above sea level |
| Displacement | 2.5 L |
| Maximum hardware power capacity | 900 kW |
| Rated take-off power | 400-600 kW |
| Continuous cruising power | 500 kW |
| Operating speed range | 5,500-6,000 rpm |
| Dry mass | 145 kg |
| Power-to-weight ratio | 2.7-4.1 kW/kg |
| Approved fuel | 95# / 98# / 100LL aviation gasoline |
| Specific fuel consumption | 260-360 g/kWh |
| TBO interval | 2,000 flight hours |
| Altitude performance | Only 10%-15% power drop at 4,000 m above sea level |
| Displacement | 2.5-3.4 L |
| Maximum hardware power capacity | 1,000 kW |
| Rated take-off power | 600-800 kW |
| Continuous cruising power | 600 kW |
| Operating speed range | 5,500-7,000 rpm |
| Dry mass | 165 kg |
| Power-to-weight ratio | 3.6-4.8 kW/kg |
| Approved fuel | 95# / 98# / 100LL aviation gasoline |
| Specific fuel consumption | 260-380 g/kWh |
| TBO interval | 2,000 flight hours |
| Altitude performance | Only 10%-15% power drop at 4,000 m above sea level |
| Displacement | 3.8-4.3 L |
| Maximum hardware power capacity | 2,500 kW (ultra-high peak power reserve) |
| Rated take-off power | 800-1,200 kW |
| Continuous cruising power | 1,000 kW |
| Operating speed range | 5,500-6,500 rpm |
| Dry mass | 195 kg |
| Power-to-weight ratio | 4.1-6.1 kW/kg (industry-leading benchmark) |
| Approved fuel | 95# / 98# / 100LL aviation gasoline |
| Specific fuel consumption | 310-460 g/kWh |
| TBO interval | 2,000 flight hours |
| Altitude performance | Only 10%-15% power drop at 4,000 m above sea level |
Every unit is equipped with large-size twin turbochargers for forced air intake compensation. Unlike naturally aspirated engines that suffer severe power attenuation at high elevations, this series limits power loss to merely 10%-15% at 4,000 m. Sufficient thrust is retained for steep climbing, high-speed cruise and heavy-load takeoff under plateau and mountainous operating environments.
The full operating band spans 5,500-8,000 rpm for the high-performance variants. Massive transient power reserve is built into the hardware, delivering rapid throttle response during vertical climb, acceleration and gust resistance, perfectly matching the dynamic power demand of high-speed manned aerial vehicles.
Inline 3/4/5-cylinder and V6 units share identical base mechanical architecture. Engineers adjust cylinder quantity, turbocharger specifications and ECU calibration only to cover the full power bandwidth from 300 kW to 1,000 kW. High part interchangeability lowers spare part stocking pressure and operator training cost.
Integrated thin-wall cast aluminum cylinder blocks eliminate redundant structural weight. Optimized lightweight treatment is applied on upgraded models such as L401B to cut mass without sacrificing structural rigidity. The flagship V601-379 achieves a peak power-to-weight ratio of 6.1 kW/kg, far exceeding traditional V-type aviation piston engines of equivalent power output. The compact footprint simplifies installation inside narrow eVTOL and aircraft nacelles, maximizing available payload and fuel capacity.
All models adopt a consistent 2,000-hour Time-Between-Overhaul cycle, eliminating differentiated overhaul scheduling for mixed fleets. Core mechanical and electrical components are cross-compatible across the lineup to streamline after-sales support.
Multi-point aviation gasoline EFI system delivers smooth, lag-free throttle modulation. No pre-heating procedure is required before startup, unlike heavy-fuel compression ignition engines. Operation remains stable under frequent takeoff, landing and speed adjustment cycles typical for manned aircraft.
- Industry Top-Tier Lightweight & Power-to-Weight Performance: Lightened casting technology cuts unit mass significantly while boosting power density. The outstanding kW/kg rating reduces empty aircraft weight, directly lifting passenger capacity, cargo load and maximum flight range for eVTOL and fixed-wing platforms.
- Complete Full-Band Power Product Matrix: The lineup provides seamless power coverage from 300 kW entry-level units up to the 1,000 kW flagship V6 model. Operators can source all required power grades from a single product family.
- Superior High-Altitude Operation Adaptability: Turbo forced induction offsets thin air at high elevations, delivering steady climbing power for mountain tourist routes and plateau commuter flights without obvious performance degradation.
- Generous Peak Power Safety Margin: Each engine's hardware maximum power capacity is substantially higher than its rated continuous output. Extra power reserve acts as a critical safety buffer during emergency scenarios.
- Simplified Ground Operation & Maintenance Workflow: Elimination of heavy-fuel cold preheating systems shortens pre-flight preparation time. Onboard ECU integrated self-diagnosis functions quickly pinpoint abnormal components.
3-6 seat intercity tilt-rotor air taxis, scenic sightseeing composite-wing manned carriers, and amphibious water-land passenger aerial vehicles. Recommended models: L401B, L501 and V601 series, leveraging lightweight high power-to-weight design to maximize passenger load and flight endurance.
Plateau mountain sightseeing aircraft, private sport planes, flight training trainers, light seaplanes and island short-haul commuter aircraft. Recommended models: L301, L401 and L501 mid-power inline variants (300-600 kW continuous output).
Performance racing aircraft, high-speed target drones and experimental high-performance flight vehicles rely on the series' high-rev instant acceleration and massive peak power reserve for extreme flight speed requirements.
6+ seat long-distance intercity commuter aircraft and large amphibious general aviation vessels select the flagship V601-379 unit to deliver sufficient thrust for heavy payload and steep climb missions.
- Fuel compatibility is restricted exclusively to aviation gasoline (95#/98#/100LL). The engines cannot operate with jet kerosene or road diesel, limiting deployment in remote areas lacking dedicated aviation gasoline supply infrastructure.
- High-displacement, high-power variants carry elevated specific fuel consumption (up to 460 g/kWh for the flagship model). Identical fuel tank capacity yields shorter endurance compared to equivalent heavy-fuel compression ignition power units.
- Official civil aviation airworthiness certification documents (EASA / CCAR) are not specified in product datasheets, creating regulatory compliance barriers for cross-border manned aircraft export business.
- Continuous high-rev operation accelerates wear on turbocharger and high-temperature exhaust components, requiring more frequent intermediate inspections compared to low-rpm heavy-fuel piston engines.
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