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US 8,201,414 B2Granted
Assistance device for transient acceleration and deceleration phases
AssigneeTurbomeca
InventorsEdgar Haehner, Gerald Senger
Life of this patent
Estimating the term…
Abstract
A turbine engine for a helicopter, including a gas generator and a free turbine driven in rotation by the gas flow generated by the gas generator is disclosed. The turbine engine further includes a motor/generator coupled to a shaft of the gas generator, to provide a quantity of additional rotational kinetic energy to the shaft during a stage of turbine engine acceleration, or to draw a quantity of rotational kinetic energy from the shaft during a stage of turbine engine deceleration.
Claims8
A turbine engine of an aircraft, comprising:
- a gas generator and a free turbine driven in rotation by the gas flow generated by the gas generator;
- a first electricity generator coupled to a shaft of the free turbine;
- a storage unit electrically connected to the first electricity generator;
- and
- an electric motor/generator electrically connected to the storage unit and mechanically coupled to a shaft of the gas generator,
- wherein the shaft of the free turbine is coupled to a rotor of a helicopter,
- wherein the storage unit supplies power to the motor/generator during a stage of turbine engine acceleration to provide a quantity of additional rotational kinetic energy to the gas generator shaft and stores a quantity of kinetic energy drawn from the gas generator shaft by the motor/generator in a form of electrical energy during a stage of turbine engine deceleration, and
- wherein the storage unit is recharged by the first electricity generator.
5 more elements
A turbine engine of an aircraft, comprising:
- a gas generator and a free turbine driven in rotation by the gas flow generated by the gas generator;
- a first electricity generator coupled to a shaft of the free turbine;
- a storage unit electrically connected to the first electricity generator;
- an electric motor/generator electrically connected to the storage unit and mechanically coupled to a shaft of the gas generator;
- and
- a converter and an electronic control device positioned between and electrically connected to the motor/generator and the storage unit,
- wherein the shaft of the free turbine is coupled to a rotor of a helicopter,
- wherein the storage unit supplies power to the motor/generator during a stage of turbine engine acceleration to provide a quantity of additional rotational kinetic energy to the gas generator shaft and stores a quantity of kinetic energy drawn from the gas generator shaft by the motor/generator in a form of electrical energy during a stage of turbine engine deceleration,
- wherein the storage unit is recharged by the first electricity generator, and
- wherein the motor/generator starts the gas generator while starting the turbine engine.
7 more elements
Dependencies are inferred from the claim text.