Hindustan Aeronautics Limited (HAL) is actively searching for an advanced aero engine for its next-generation supersonic lead-in fighter trainer, the HLFT42. The company seeks a high-thrust, fuel-efficient, and reliable turbofan engine to power this cutting-edge training aircraft. This article explores the specifications of HAL’s requirements and potential vendors that can provide suitable engine solutions.
HLFT42: A Next-Generation Fighter Trainer
The HLFT42 is a twin-cockpit, supersonic, fly-by-wire aircraft designed to provide advanced jet training to student pilots. The aircraft must be capable of high-performance aerobatic maneuvers, ensuring effective training for future fighter pilots. It requires an engine with high thrust, reliability, and cost-effective maintenance, enabling four sorties per day over its total technical life.
HAL’s Engine Requirements for HLFT42
Performance Specifications
- Maximum Continuous Thrust: 21,350 – 22,500 lbf (95 – 100 kN) @ ISA SLS
- Specific Fuel Consumption (SFC): < 70g/s/kN
- Operational Endurance: 8 hours (preferable engine continuous run)
- Aerobatic Capability: Capable of sustained high-g maneuvers
- Time Between Overhaul (TBO): Minimum 2,000 flight hours
- Total Technical Life (TTL): More than 6,000 flight hours
- Maintenance: Low cost and minimal downtime
Aircraft Operating Envelope
- Maximum Speed: Mach 1.8
- Max Calibrated Airspeed: 1,400 km/h (750 knots)
- Min Calibrated Airspeed: Stable operation till 150 km/h (80 knots)
- Max Flight Altitude: 18 km (60,000 feet)
Engine Type
- Type: Turbofan with bypass & afterburner, FADEC controlled, self-contained lubrication system
- Thrust-to-Weight Ratio: Minimum 8:1
- Bleed Air Availability: Extraction required from both high-pressure (HP) and low-pressure (LP) compressor stages
- Fuel Type: Aviation kerosene IS 1571-2008 / Jet A-1 / JP-5 / JP-8
- Engine Control: Dual-channel FADEC with in-air relight capability
- Physical Dimensions:
- Max Length: 158 inches (4.0 meters)
- Max Diameter: 36 inches (0.9 meters)
- Max Dry Weight: 2,650 lbs (1,200 kg)
Potential Engine Vendors for HLFT42
Below is a comparison of potential engine vendors that offer systems similar to HAL’s requirements.
| Vendor | Engine Model | Thrust (kN) | SFC (g/s/kN) | TBO (hours) | TTL (hours) | Dimensions (LxD, meters) | Dry Weight (kg) |
|---|---|---|---|---|---|---|---|
| General Electric | F404-GE-IN20 | 85 kN | ~78 | 2,000 | 6,000 | 3.9 x 0.9 | 1,200 |
| General Electric | F414-GE-INS6 | 98 kN | ~70 | 2,000 | 6,000 | 3.9 x 0.9 | 1,200 |
| Safran | M88-4E | 75 kN | ~70 | 2,000 | 6,000 | 3.5 x 0.7 | 1,100 |
| Rolls-Royce | EJ200 | 90 kN | ~65 | 3,000 | 9,000 | 4.0 x 0.9 | 990 |
| Klimov | RD-33MK | 88 kN | ~79 | 2,000 | 4,000 | 4.2 x 1.0 | 1,150 |
Comparison: GE F414-GE-INS6 vs. Rolls-Royce EJ200
GE F414-GE-INS6
- Closely meets HAL’s thrust requirement (98 kN within 95-100 kN range).
- SFC is within HAL’s efficiency requirement (~70 g/s/kN).
- TBO of 2,000 hours aligns with HAL’s expectation.
- TTL of 6,000 hours meets HAL’s specifications.
- Dimensions (3.9m x 0.9m) fit within HAL’s constraints.
- Will be assembled in India by HAL, ensuring strategic and logistical advantages.
Rolls-Royce EJ200
- Slightly lower thrust (90 kN), though still viable.
- Superior SFC (~65 g/s/kN), making it more fuel-efficient.
- Longer TBO (3,000 hours) and TTL (9,000 hours), reducing maintenance frequency.
- Dimensions (4.0m x 0.9m) fit HAL’s constraints.
- Not currently planned for Indian assembly, potentially increasing acquisition costs.
| HAL’s Requirement | Specification | GE F414-GE-INS6 | Rolls-Royce EJ200 |
|---|---|---|---|
| Maximum Continuous Thrust (kN) | 95 – 100 | 98 | 90 |
| Specific Fuel Consumption (SFC) (g/s/kN) | < 70 | ~70 | ~65 |
| Time Between Overhaul (TBO) (hours) | Minimum 2,000 | 2,000 | 3,000 |
| Total Technical Life (TTL) (hours) | More than 6,000 | 6,000 | 9,000 |
| Maximum Length (meters) | 4.0 | 3.9 | 4.0 |
| Maximum Diameter (meters) | 0.9 | 0.9 | 0.9 |
| Maximum Dry Weight (kg) | 1,200 | 1,200 | 990 |
| Aerobatic Capability | Sustained high-g | Yes | Yes |
| Operational Endurance | 8 hours | Compatible | Compatible |
| Bleed Air Availability | HP & LP stages | Available | Available |
| Fuel Type | Jet A-1 / JP-5 / JP-8 | Jet A-1 / JP-5 / JP-8 | Jet A-1 / JP-5 / JP-8 |
| Engine Control | Dual FADEC | Dual FADEC | Dual FADEC |
| Thrust-to-Weight Ratio | Minimum 8:1 | ~8.1:1 | ~9.1:1 |
| Maintenance | Low cost, minimal downtime | Assembled in India, easier logistics | Lower lifecycle cost, longer TBO |
HAL’s search for an ideal aero engine for the HLFT42 is a crucial step in advancing India’s fighter training capabilities. The final choice will significantly impact the aircraft’s performance, operational efficiency, and long-term sustainability. By evaluating key vendors and engine solutions, HAL aims to equip the HLFT42 with a world-class propulsion system, ensuring optimal training for the next generation of fighter pilots.