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Turbomeca Turmo

The Turbomeca Turmo is a family of turboshaft engines developed by the French manufacturer Turbomeca (now part of the Safran Group) specifically for helicopter propulsion, featuring a free-turbine design that separates the power turbine from the gas generator for improved efficiency and control.^[1]^[2] Originating as a derivative of the earlier Turbomeca Artouste engine, the Turmo series was conceived in 1959 and entered production in 1963, marking it as the first turboshaft to incorporate the free-turbine principle, which allows the output shaft to rotate independently of the core engine speed.^[2] Early development included licensing to Bristol Siddeley in the UK, where it was adapted as the Nimbus for helicopters like the Scout and Wasp.^[1] Key variants include the Turmo IIIC, rated at 1,550 shaft horsepower (shp), and the Turmo IV, which delivers 1,575 shp (1,175 kW), with the Turmo III C4 variant providing 1,340 horsepower and weighing between 225 and 300 kg.^[1]^[2] These engines typically feature a single-stage axial compressor followed by a two-stage centrifugal compressor and a two-stage power turbine.^[1] The Turmo engines powered prominent helicopters such as the Aérospatiale SA 330 Puma, which used two Turmo IV units and saw 697 units produced from 1968 to 1987 for military operators including the French Army, Royal Air Force, and various export customers,^[3] and the Sud Aviation Super Frelon, equipped with three Turmo IIIC engines.^[1]^[2] Additional applications included South African Defence Force variants of the Puma built by Armscor.^[4] Later models like the Turmo III C4 on the Puma were eventually superseded by more advanced Safran Mékila engines offering 1,590 to 1,660 horsepower.^[2]

Overview

Introduction

The Turbomeca Turmo is a family of turboshaft engines developed and manufactured by the French company Turbomeca, now part of Safran Helicopter Engines, primarily for powering helicopters.^[5] These engines span a power output range of approximately 300 kW to 1,200 kW (400 to 1,600 shp), enabling their use in a variety of light to medium helicopters during the mid-20th century.^[6] The Turmo family derives directly from the earlier Turbomeca Artouste engine, which originated as an auxiliary power unit in the late 1940s but was adapted into a full turboshaft configuration for rotorcraft propulsion.^[7] This evolution introduced a free power turbine design, improving efficiency and reliability over single-shaft predecessors like the Artouste.^[6] A turboprop variant, such as the Turmo III D, was also produced for fixed-wing applications, notably in the Bréguet 941 STOL transport aircraft.^[8] Licensed production of Turmo engines occurred in several countries, including Romania as the Turmo IV-CA by Turbomecanica and in China as the WZ-6 by the Changzhou Lanxiang Machinery Works for local helicopter programs.^[9] Later versions involved joint manufacturing with Rolls-Royce under the Rolls-Royce Turbomeca partnership, particularly for British applications like the Puma helicopter.^[1] As one of the earliest successful French turboshaft designs, the Turmo entered production in 1963 and service in the mid-1960s, playing a pivotal role in advancing helicopter technology through the 1970s and 1980s, powering both military and civilian aircraft before being largely superseded by the more powerful Makila series in subsequent decades.^[6]^[2]

Design Principles

The Turbomeca Turmo family employs a two-shaft configuration, consisting of a gas generator section—comprising the compressor, annular combustor, and gas generator turbine—that operates independently of the free power turbine section, which drives the output shaft to deliver mechanical power to the rotor or propeller.^[10]^[11] This design enhances operational flexibility and efficiency in variable-load applications like helicopters, as the power turbine speed can be optimized separately from the gas generator.^[6] Early Turmo models, such as the Turmo I and II, featured a single-stage centrifugal compressor to achieve adequate pressure ratios in a compact package suitable for initial helicopter power needs.^[1] Later variants, including the Turmo III and IV series, evolved to a single-stage axial compressor followed by a single-stage centrifugal stage, improving airflow efficiency and overall pressure ratio while maintaining a small footprint.^[10]^[11] The combustion system utilizes an annular reverse-flow combustor, which promotes compact sizing, even fuel distribution, and reliable ignition through vaporizing-type injection via a rotating wheel.^[11] This arrangement supports stable operation across a wide range of conditions, minimizing pressure losses and emissions precursors. The turbine assembly includes a two-stage axial gas generator turbine that extracts energy to drive the compressor, constructed from high-temperature nickel-based alloys to withstand exhaust gas temperatures exceeding 900°C.^[10] The free power turbine comprises a single axial stage, also using nickel alloys, to convert the gas stream's energy into shaft power with high efficiency and reduced vibration.^[1]^[11] Accessory systems are integrated via a rear-mounted gearbox that powers essential components, including the starter/generator, fuel and oil pumps, and tachometer drives, while incorporating hydromechanical fuel control for precise metering.^[11] Air bleed provisions from the compressor enable anti-icing of the inlet and cabin pressurization in applicable installations, with flows up to 250 g/s at 520 kPa and 280°C.^[11] A key innovation in the Turmo design is its modularity, allowing scalable power outputs from approximately 200 kW in early versions to over 1,000 kW in advanced models through shared core architecture and component upgrades, facilitating cost-effective family development.^[6] Additionally, initial Turmo variants were adapted as gas producers to supply compressed air for tip-jet rotor propulsion in experimental helicopters, demonstrating versatility beyond direct shaft drive.^[10]

Development

Origins and Early Versions

The Turbomeca Turmo family of turboshaft engines originated in the early 1950s at Turbomeca, evolving from the company's earlier Artouste auxiliary power unit design to meet the growing demand for dedicated helicopter propulsion. As the first free-turbine turboshaft engine developed for helicopters, the Turmo represented a significant advancement in gas turbine technology for rotorcraft, enabling more efficient power transmission to the rotor via a separate power turbine.^[7]^[12]^[1] The initial Turmo I prototype delivered approximately 200 kW (270 shp) and underwent ground testing in the mid-1950s, with early applications including experimental ground vehicles like the Renault Étoile Filante, where it powered a land speed record attempt in 1956. Early development focused on a centrifugal compressor configuration, though reliability concerns with compressor materials prompted iterative improvements through advanced alloys to enhance durability under high-stress conditions. These efforts addressed initial challenges in sustaining consistent performance during prolonged operation.^[13]^[6] The Turmo entered production in 1963, marking Turbomeca's breakthrough in turboshaft technology and France's emergence as a key player in helicopter engine manufacturing. Its operational debut came in 1959 with the first flight of the Sud-Aviation SE.3200 Frelon prototype, a large transport helicopter powered by three Turmo III engines, demonstrating the engine's viability for powering experimental and small rotorcraft configurations.^[14]^[2] Early collaboration discussions with British firms, including Bristol Siddeley (later acquired by Rolls-Royce), began in the late 1950s and led to licensed production of the Turmo design as the Nimbus engine starting in the early 1960s, facilitating international adoption and joint development for helicopters like the Westland Scout. This partnership underscored Turbomeca's strategy to expand the Turmo's global footprint while overcoming domestic production constraints.^[1]

Evolution to Advanced Models

The Turmo III series marked a significant advancement in the engine's design, introducing a single-stage axial followed by a single-stage centrifugal compressor configuration that enabled power outputs ranging from approximately 600 kW to 1,100 kW, suitable for medium-lift helicopters.^[14] This series first powered the Sud Aviation SA 321 Super Frelon prototype, achieving its maiden flight on December 7, 1962, with three Turmo IIIC2 engines each rated at around 1,320 shp (985 kW).^[15] The design emphasized reliability and scalability, building on earlier centrifugal compressor roots while incorporating a two-stage gas generator turbine to handle increased loads. Military requirements drove further refinements in the Turmo III lineup, particularly the IIIC4 variant developed specifically for the Aérospatiale SA 330 Puma helicopter, which entered service in 1968.^[3] Rated at 884 kW (1,185 hp) per engine, the IIIC4 featured enhanced cooling systems and automatic power management to optimize hot-and-high performance, allowing the Puma to maintain full rotor power across diverse environmental conditions without derating.^[16] This adaptation addressed operational demands in challenging terrains, such as high-altitude or tropical environments, contributing to the Puma's versatility in troop transport and search-and-rescue roles. International partnerships accelerated production and variant dissemination, with Rolls-Royce collaborating with Turbomeca from the late 1960s to license-build and refine the Turmo III C4 for joint Anglo-French projects like the Puma.^[17] By 1970, this cooperation extended to full joint manufacturing, enabling broader export and integration into British and Commonwealth fleets, while maintaining the engine's core free-turbine architecture for improved responsiveness. In the 1970s, the Turmo reached its developmental peak with the IV series, delivering up to 1,200 kW through optimizations like refined airflow paths and early adoption of electronic fuel control elements for enhanced efficiency and reduced pilot workload.^[6] Variants such as the Turmo IVC powered upgraded Pumas, incorporating a two-stage power turbine for smoother torque delivery and better fuel economy under varying loads. Technological enhancements across these models included reverse-flow annular combustors, which minimized size and weight while promoting complete fuel burn for lower emissions and noise.^[11] Production scaled rapidly, with over 2,500 Turmo units manufactured by the mid-1980s to meet global demand for Super Frelon and Puma fleets.^[18] However, by the 1990s, the series began phasing out in favor of the more powerful Turbomeca Makila, which offered superior power-to-weight ratios and modular maintenance for newer helicopter generations like the Super Puma.^[19]

Variants

Core Turboshaft Variants

The Turbomeca Turmo I was the initial turboshaft variant in the family, delivering 200 kW (270 shp) continuous power through a single-stage centrifugal compressor design. Development began in the late 1950s, with early units produced around 1960–1963. It powered small helicopters and established the free-turbine architecture central to the series. The Turmo II followed with 300 kW (400 shp) output, incorporating minor efficiency enhancements such as refined airflow management for better fuel economy over the predecessor. It found application in early Alouette helicopter models, supporting the transition to more reliable medium-duty operations. The Turmo III series represented a major step forward, featuring an axial-centrifugal compressor configuration that improved compression efficiency and power density. The IIIA variant provided 440 kW (590 shp), while the IIIB provided 520 kW (700 shp) and the IIIC 740 kW (992 shp); subsequent upgrades in the IIIC2 through IIIC7 subvariants delivered 820–1,000 kW (1,100–1,340 shp), with specialized ratings like the IIIC4's military output of approximately 880 kW (1,180 shp) optimized for hot climates through enhanced cooling and material tolerances. Over 1,000 Turmo III units were produced, reflecting its widespread adoption in medium-lift helicopters.^[2]^[1]^[20] Introduced in 1972 for upgrades to the Puma helicopter, the Turmo IV addressed demands for higher performance in civil and military roles. The IVB civil version rated at 1,200 kW emphasized reliability for commercial transport, while the IVC military variant achieved 1,300 kW takeoff power with reinforced components for tactical operations.^[21]^[3]

Turboprop and Specialized Variants

The Turbomeca Turmo III D and III E variants were adapted as turboprop engines, featuring a reduction gearbox to drive propellers for fixed-wing applications. These versions delivered power outputs ranging from 965 to 1,045 kW (1,294 to 1,401 shp), enabling short takeoff and landing (STOL) capabilities in transport aircraft. Specifically, the Turmo III D3 powered the Bréguet 941 STOL transport, with four engines each providing approximately 965 kW (1,294 shp) to support operations on unprepared airstrips.^[22] An experimental turboprop derivative, the Turmo III F, was developed with a power rating of approximately 1,118 kW (1,500 shp) for fixed-wing testing, focusing on performance evaluation in non-helicopter configurations. This variant explored enhancements in efficiency and integration for broader aviation uses beyond standard turboshaft roles. Licensed international productions expanded the Turmo's reach, particularly in the 1980s. In China, the WZ-6 was a reverse-engineered version of the Turmo IIIC6, rated at 888 kW (1,190 shp) for continuous operation and up to 1,215 kW (1,630 shp) maximum, produced for powering the Z-8 helicopter family.^[23] In Romania, the Turmo IV-CA was manufactured under license by Turbomecanica for the IAR 330 Puma helicopter, delivering 1,160 kW per engine and supporting local assembly to meet national defense needs.^[9] Specialized adaptations of the Turmo included gas producer configurations, where the engine supplied high-mass-flow hot gas and compressed air to tip-jet rotor systems, eliminating the need for a mechanical transmission in certain experimental helicopters. The proposed Turmo XII represented an advanced upgrade concept, targeting around 1,200 kW (1,600 shp) for non-aerial applications such as rail propulsion, though it saw limited development and no aviation production. The T 2000 Turbotrain used earlier Turmo III engines.^[24] Limited modifications for marine and industrial uses were explored, leveraging the Turmo's modular design for ground-based power units, but these saw minimal adoption compared to aviation applications.

Applications

Helicopter and Aviation Uses

The Turbomeca Turmo engine found its primary application in heavy-lift helicopters, notably powering the Sud-Aviation SA 321 Super Frelon with three Turmo IIIC3 turboshafts, enabling its entry into service in 1966 for naval and anti-submarine warfare roles.^[25] This configuration supported the helicopter's multi-role capabilities, including troop transport and maritime patrol, with the engines providing reliable power for operations in diverse environments.^[15] In medium twin-engine helicopters, the Turmo IVC became central to the Aérospatiale SA 330 Puma, which debuted in 1968 and saw over 700 units built primarily for military transport duties.^[26] The twin Turmo IVC setup delivered balanced performance for carrying up to 16 troops or equivalent cargo, contributing to the Puma's versatility in assault and utility missions across global operators.^[27] A licensed derivative, the Bristol Siddeley Nimbus (based on the Turmo), powered British Westland Scout and Wasp helicopters, entering service in the 1960s for naval and anti-submarine roles.^[12] Beyond helicopters, the Turmo IIID turboprop variant powered the fixed-wing Bréguet 941, a short takeoff and landing transport prototype that first flew in 1961, with four units constructed by 1967 for STOL evaluation.^[22] This innovative use demonstrated the engine's potential in aviation beyond pure turboshaft roles, emphasizing efficient short-field operations. Operationally, Turmo-powered Pumas participated in combat during the Falklands War of 1982, serving both British and Argentine forces in transport and evacuation missions.^[28] Exported to over 40 countries, these helicopters and their engines supported military and civilian aviation worldwide, with the Puma family alone accumulating millions of flight hours by the late 20th century.^[3] Later upgrades often involved engine replacements with successors like the Makila series to extend service life and enhance performance.^[29]

Ground and Experimental Applications

The Turbomeca Turmo engine found significant application in experimental rail propulsion during the 1960s and 1970s, particularly in French high-speed train prototypes developed to explore gas turbine technology for passenger rail. The Turmo III variant, rated at 860 kW for rail traction, powered the Experimental Gas Turbine Set introduced in 1967 and later the first-generation ETG Turbotrain, which entered service in March 1970 on the Paris-Caen-Cherbourg route.^[30] This prototype, accommodating 200 passengers, achieved a maximum speed of 180 km/h through a Voith hydraulic transmission system driving the wheels.^[30] The second-generation RTG Turbotrain, also equipped with the Turmo III, expanded testing to routes like Lyon-Strasbourg, reaching 200 km/h in service with up to two trailers and capacity for 300 passengers.^[30] A landmark experimental use came with the TGV 001 prototype in 1972, SNCF's inaugural high-speed train testbed, which integrated four Turmo III G engines across two power cars for a total output of approximately 3,760 kW.^[30] This configuration enabled dynamic testing of vehicle aerodynamics, braking, and traction on dedicated tracks, culminating in a world record speed of 318 km/h on December 8, 1972—the fastest for a gas turbine-powered rail vehicle at the time—before the project shifted to electric propulsion for production TGVs.^[30] The TGV 001's design emphasized modular power cars with the Turmo's free-turbine architecture to support high-speed stability and efficiency evaluations.^[30] Beyond rail, the Turmo featured in automotive experiments during the 1950s, notably the Renault Étoile Filante land speed record vehicle, a collaboration between Renault and Turbomeca to demonstrate gas turbine viability in road applications.^[31] Initiated in 1954, the project mounted a Turmo I turbine producing 270 hp at 28,000 rpm, fueled by kerosene and paired with a Transfluide hydraulic transmission.^[31] The streamlined, lightweight prototype achieved multiple records in 1956 on the Bonneville Salt Flats, including an average speed of 308.85 km/h in the Class C flying mile, highlighting the engine's high power-to-weight ratio for experimental high-speed terrestrial propulsion, though no production vehicles resulted.^[31] In industrial contexts, Turmo derivatives supported stationary roles such as compressor drives, leveraging the engine's robust gas generator for reliable power in non-transport settings like oil and gas operations, though these applications remained limited compared to aviation uses. Experimental testing in the 1960s and 1970s extended to altitude simulation for engine validation, where Turmo units drove rigs to replicate high-altitude conditions, aiding development of subsequent variants.

Specifications

General Characteristics

The Turbomeca Turmo IIIC7 is a two-shaft turboshaft engine designed for helicopter applications.^[25] It measures 1,820 mm (71.7 in) in length and 716 mm (28.2 in) in diameter. The dry weight is 325 kg (717 lb).^[32] The engine delivers a take-off power output of 1,175 kW (1,576 shp) and a maximum continuous power of 993 kW (1,332 shp) at the gearbox.^[25] Additional parameters include a compressor pressure ratio of 5.8:1 and a turbine inlet temperature of 1,050 °C.

Components

The Turbomeca Turmo IIIC7 turboshaft engine features a modular design with key subsystems integrated for efficient power generation in helicopter applications. The compressor section consists of a single-stage axial low-pressure compressor followed by a single-stage centrifugal high-pressure compressor, both driven by a two-stage axial gas generator turbine. This configuration achieves an overall pressure ratio of approximately 5.8, with the axial stage providing initial compression and the centrifugal stage delivering higher pressure for optimal airflow into the combustor.^[33]^[34] The combustor is an annular reverse-flow type, which promotes compact packaging and uniform combustion by directing hot gases rearward around the flame tube before reversing into the turbine. This design enhances mixing and reduces emissions while maintaining stable burning across operating conditions. Fuel is introduced through multiple injectors to ensure even distribution and efficient energy release.^[35] The turbine assembly includes a two-stage axial gas generator turbine that extracts energy from the hot gases to drive the compressor, with blades constructed from high-temperature materials like Inconel for durability under thermal stress. Downstream is a two-stage free power turbine, independent of the gas generator, which converts remaining energy into mechanical shaft power; adjustable stator vanes on the power turbine allow optimization of airflow and torque response for varying loads.^[34] Power transmission occurs via a planetary reduction gearbox that steps down the high-speed turbine output to a 6,000 rpm shaft speed suitable for helicopter rotor systems. The gearbox incorporates epicyclic gears for compact, high-torque reduction and includes accessory drives to power hydraulic pumps, electrical generators, and other ancillary systems.^[35] Air intake is via a curved inlet duct designed for helicopter nose or side mounting, often equipped with an inertial particle separator to protect the compressor from sand and debris ingestion in operational environments. Exhaust is directed axially rearward to minimize infrared signature and integrate seamlessly with helicopter tail structures.^[36] Engine control is managed by a hydro-mechanical governor that regulates fuel flow and gas generator speed for stable operation, maintaining constant output under varying conditions through feedback from speed sensors and hydraulic actuation. Subsequent Turmo IV series models introduced electronic upgrades for enhanced precision and fault tolerance.^[37]

Performance

The Turbomeca Turmo IIIC7 turboshaft engine exhibits robust power output characteristics suited for medium-lift helicopter applications. At sea level under standard conditions, it achieves a take-off power of 1,175 kW (1,576 shp) at a gas generator speed of 15,500 rpm, enabling reliable performance in demanding takeoff and climb phases.^[38] Altitude performance is derated to maintain operational integrity, with power reduced to 800 kW at 3,000 m elevation, further penalized on hot days under ISA+30°C conditions to account for reduced air density and increased ambient temperatures. This derating ensures safe operation in high-altitude or tropical environments without exceeding thermal limits.^[39] Fuel efficiency is a key strength, with specific fuel consumption (SFC) rated at 0.603 lb/hp-hr.^[40] Endurance metrics demonstrate solid reliability, featuring a time between overhauls of 2,000 hours, supported by mean time between failures (MTBF) data of 500 hours derived from operational experience on Aérospatiale Puma helicopters.^[41] Operational limitations include a maximum turbine inlet temperature of 1,050 °C and an exhaust gas temperature of 650 °C, which protect component integrity during extended high-power runs.^[39] Compared to its predecessor, the Turbomeca Artouste, the Turmo IIIC7 offers approximately 20% improved SFC through advanced compressor and combustor designs, though early models exhibited higher noise levels that were mitigated in subsequent variants via refined exhaust systems.^[7]

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ARTOUSTE engine family (Plate I). On this type of engine, the main objectives of the control system are - besides starting -. 1. to keep the engine rotational ...Missing: derivation | Show results with:derivation
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Aérospatiale SA 321GM Super Frelon
May 26, 2018 · Turboméca Turmo IIIC7 o výkonu 1155 kW / 1570 k; Objem palivových ... Turboméca Turmo IIIC7, power 1549 shp; Fuel Tank Capacity: 874 Imp ...
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Janes.aero.Engine - PDFCOFFEE.COM
Evolution of the PT6A turboprop: power/weight ratio and specific fuel consumption. ... Specific Fuel Consumption At T-O rating: Turmo IIIC3 and E3 101.9 µg ...
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Military Turboshaft/Turboprop Specifications. (sorted by engine model). Manufacturer, Model, Application(s), Power, SFC, Airflow, OPR, Number ...Missing: details | Show results with:details
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[PDF] aircraft accident report 2/85 - GOV.UK
Jun 10, 1985 · Schematic diagram of Turbomeca Turmo IVC Turboshaft engine. Appendix 3. Detailed section from the engine instrument panel. Appendix 4. SA330J ...Missing: specifications | Show results with:specifications