Safran Ardiden
| Industry | Aerospace |
|---|---|
| Founded | 2000 |
| Products | Turboshaft engines (Ardiden series) |
| Owner | Safran |
| Website | www |
The Safran Ardiden represents a turboshaft engine developed by Safran Helicopter Engines intended for use in both single and twin-engine helicopter platforms. Originating in 2003 as an upgraded iteration of the Turbomeca TM 333, it achieved its inaugural run in 2005 and officially entered operational service by 2007.
The Ardiden 1 Shakti variant is utilized in Indian rotorcraft such as the HAL Dhruv, HAL Prachand, and HAL Light Utility Helicopter. Meanwhile, the higher-powered Ardiden 3 model equips helicopters including the Avicopter AC352 and Kamov Ka-62.
Development
In 1961, Turbomeca granted a license to Hindustan Aeronautics Limited to produce the Turbomeca Artouste turboshaft engine for Indian models like the HAL Chetak and HAL Cheetah helicopters.
By September 2000, HAL had engaged Turbomeca to enhance the power output of the ALH’s existing TM 3332B2 engine. This upgrade aimed to increase power beyond . By January 2002, Turbomeca commenced development of the Ardiden TM3332C2 targeted at helicopters, unveiling it as the Shakti during the Paris Air Show. Following the lifting of US sanctions after India’s 1998 nuclear tests, HAL collaborated on co-development and assembly activities.
This new design replaced the TM3332B2’s initial two axial compressor stages with a centrifugal compressor and introduced a two-stage power turbine equipped with dual-channel FADEC. The engine was projected to enter service by 2005, with market estimates anticipating demand for approximately 1,500 units over a 15-year span.
By mid-2002, Turbomeca was preparing to launch development of the (1,200 hp) engine variant, with HAL holding an 11% stake specifically for the ALH program, later renamed Dhruv. The TM333 was derated from for use on the Dhruv; Ardiden family members included the 1H Shakti, derated from , alongside variants such as the Ardiden 1A for the Eurocopter EC155HP+ and Ardiden 2K designed for the Agusta-Bell AB.139. Positioned between the Turbomeca Arriel and Turbomeca Makila engines, it targeted medium twin-engine helicopters in the 5-6 ton category.
With a price point near $500,000, it was roughly 40% less expensive than comparable engines like Honeywell/Rolls-Royce’s LHTEC CTS800 and MTU/Turbomeca/R-R’s MTR390. Initial testing was scheduled for early 2004, aiming for certification by late 2005 and service introduction by 2006.
The program was officially launched in February 2003 at Aero India with a significant order from HAL intended for helicopters weighing between 6 to 6.5 tons. HAL contributed approximately ten percent of component manufacturing.
By October 2005, Turbomeca had completed initial testing in Tarbes with plans targeting a first flight around July 2006. HAL maintained an 11% development share and produced critical components including the gearbox and power turbine. The design featured single-crystal high-pressure turbine blades combined with advanced ceramic coatings that allowed operation without cooling systems, supporting a potential performance growth margin of up to 20%.
India held a 19% stake in development as the Shakti underwent its maiden test flight on the Dhruv on August 16, 2007. By late that year, HAL began integrating Shakti engines into newly produced Dhruv helicopters.
The Ardiden 3G variant secured certification in June 2017; by 2018, over 250 units of Ardiden 1 engines were actively deployed. As of September 2019, Ardiden 1 engines had accumulated more than 200,000 flight hours while Ardiden 3C/3G versions had surpassed over 10,000 hours in testing.
Turboprop variant
As of April 2019, Safran was advancing a turboprop adaptation of the Ardiden engine, designed to rival the Pratt & Whitney Canada PT6 and General Electric Catalyst. This development stems from its Tech-TP demonstrator developed under the EU’s Clean Sky 2 initiative. The initial ground test took place on 12 June in Tarnos, showcasing a fully integrated propulsion system comprising the nacelle, air intake, and propeller. The accessory gearbox and propeller controller utilize cutting-edge electric technology.
This turboprop is intended primarily for upcoming European UAV platforms, with the gearbox engineered in collaboration with ZF Luftfahrttechnik and the propeller supplied by MT-Propeller. The FADEC system governs both engine output and propeller blade angle, allowing operation at altitudes reaching 13,716 meters (45,000 feet). The Tech TP’s design emphasizes compactness and reduced weight, targeting a 15% improvement in fuel efficiency relative to existing engines.
On 21 July 2020, Safran and ZF formalized an agreement to initiate flight trials of the Ardiden 3TP, rated between 1,700 and 2,000 shp (1,260–1,490 kW), starting in 2022. The first application is planned for the 11-tonne EuroMALE UAV, with its maiden flight expected in 2024, before expanding into civil aviation sectors.
Design
The Ardiden 1 series produces , whereas the Ardiden 3 series generates , catering to both single- and twin-engine helicopter configurations.
Its design incorporates a two-stage centrifugal compressor, a reverse-flow annular combustor, followed by a single-stage axial gas generator turbine. Power is then delivered through a two-stage axial free turbine, which transmits torque forward via a concentric shaft. Engine control is maintained through a dual-channel digital engine electronic control unit.
Variants and applications
| Variant | Certification | Application |
|---|---|---|
| Ardiden 1H | 20 December 2007 | HAL Dhruv HAL Prachand |
| Ardiden 1H1 | 11 March 2009 | |
| Ardiden 1U | 31 October 2019 | HAL Light Utility Helicopter |
| Ardiden 3G | 12 June 2017 | Kamov Ka-62 |
| Ardiden 3C / WZ16 | 5 April 2018 | Avicopter AC352 |
Specifications
| Parameter | Ardiden 1 | Ardiden 3 |
|---|---|---|
| length | 1,250 mm (49 in) | 1,244–1,285.4 mm (48.98–50.61 in) |
| height × width | 694×519 mm (27.3×20.4 in) | 648×640–655.9 mm (25.51×25.20–25.82 in) |
| weight | 205 kg (452 lb) | 215–226.6 kg (474–500 lb) |
| compressor | Two centrifugal stages | |
| combustor | Reverse-flow annular combustor | |
| turbine | One high-pressure stage, two power stages | |
| takeoff power | 938–1,032 kW (1,258–1,384 hp) | 1,177–968 kW (1,578–1,298 hp) |
| power-to-weight ratio | 4.58–5.03 kW/kg (2.79–3.06 hp/lb) | 5.47–4.27 kW/kg (3.33–2.60 hp/lb) |