Safran

Commissariat &#xc0; L'&#xc9;nergie Atomique Et Aux &#xc9;nergies Alternatives

Arianegroup Sas

Safran Nacelles

Holcim Technology Ltd

Armines

Samer Maalouf

Denis Clodic

Hugo Pierre Mohamed Jouan

Nicolas Claude Parmentier

Pierre-Alain Marie Cyrille Lambert

Ephraïm Toubiana

Etienne Yung Tang

Nawal Jaljal

Pierre Dumoulin

Nicolas Tauveron

Thierry Sibilli

Pierre-Alain Lambert

Carlos Alberto Cruz

Davide Duri

Adrien Cahuzac

Ibrahima Noba

Louis-Vianney Mabille De La Paumeliere

Thomas Weimer

Quentin Holka

Jean-Nicolas Pierre Bouchout

Urs Andreas Herzog

Thomas Lamare

Elias Boulawz Ksayer

The invention relates to a system () for controlling the temperature of a heat transfer fluid (F) configured to transfer heat to a fluid to be heated (Q) originating from a cryogenic tank (R), the control system () comprising: a loop () for circulating the heat transfer fluid (F), comprising an engine branch () and a tank branch (); a first engine heat exchanger (), configured to heat the heat transfer fluid (F) to a second temperature (T) above a maximum operating temperature (Tmax); a mechanical pump () configured to circulate the heat transfer fluid (F) in the circulation loop (), such that, in a second engine heat exchanger (), a first part of the heat is transferred from the heat transfer fluid (F) to the fluid to be heated (Q) and the heat transfer fluid (F) is cooled to a third temperature (T) below the maximum operating temperature (Tmax), before it leaves the engine enclosure (EN-M).

System for controlling the temperature of a heat transfer fluid in a circulation loop, and temperature control method

A heating turbomachine for a fuel-conditioning system, which is configured to supply an aircraft turboshaft engine with fuel from a cryogenic tank. The heating turbomachine comprising: compressor; a turbine; a combustion chamber which is configured to discharge a flow of exhaust air loaded with heat energy and to rotate the turbine; at least one fluid circuit in which a heat-transfer fluid circulates in the downstream direction; and at least one post-combustion heat exchanger which is mounted in the fluid circuit and is configured to extract heat energy from the exhaust air chamber flow between the combustion and the turbine.

Heating turbomachine for a fuel-conditioning system configured to supply an aircraft turboshaft engine with fuel from a cryogenic tank

A system for heating cryogenic fuel includes a storage take, a supply line, a closed circuit, a cryogenic fuel heat exchanger, one or more working fluid heat exchangers, and a controller The storage tank stores the cryogenic fuel in a liquid state. The supply line connects the storage tank to a combustion chamber of an aircraft turbine engine. The closed circuit circulates a heat-transfer fluid. The cryogenic fuel heat exchanger heats the cryogenic fuel by the heat-transfer fluid. The closed circuit includes a pump for circulating the heat-transfer fluid and a closed expansion vessel connected to the closed circuit. The controller controls the pump to ensure a heat-transfer fluid flow rate inside the closed circuit so that the closed expansion vessel keeps the heat-transfer fluid circulating in the closed circuit at a pressure such that the heat-transfer fluid remains in the liquid state and does not change phase.

Installation for heating a cryogenic fuel

Disclosed is a fuel conditioning system (SC) configured to supply an aircraft turbine engine using fuel (Q) from a cryogenic tank (RC), the conditioning system (SC) comprising at least one pumping turbomachine (), a first heat exchanger () configured to heat the fuel (Q) in the fuel circuit (CQ) by circulating an air stream (A), and at least one heating turbomachine () configured to supply an air flow (A) to the first heat exchanger (), the heating turbomachine () comprising an air intake compressor (), a combustion chamber () and an air exhaust turbine () configured to drive the air intake compressor (), the combustion chamber () being supplied with air taken from the air flow (A) and with the fuel (Q) from the fuel circuit (CQ).

Fuel conditioning system and method configured to power an aircraft turbine engine using fuel from a cryogenic tank

A fuel conditioning system configured to supply an aircraft turbine engine with fuel from a cryogenic tank. The fuel circuit comprising a buffer tank for supplying the turbine engine and a plurality of compression modules configured to supply the buffer tank, each compression module comprising an elementary tank of fixed volume, an elementary heat source configured to increase the temperature of the fuel in the elementary tank in an isochoric manner, an inlet valve connecting the elementary tank to an upstream part of the fuel circuit, an outlet valve connecting the elementary tank to the buffer tank, and a venting valve connecting the elementary tank to the cryogenic tank via a return circuit in which a gaseous stream circulates.

Fuel conditioning system and method configured to supply an aircraft turbine engine with fuel from a cryogenic tank

A heat exchange system of a turbomachine, includes a heat exchanger including a support wall, a plurality of fins each extending in a radial direction from a radially outer surface of the support wall, and a cover covering the fins, wherein the cover is connected, upstream in the direction of flow of the air flow, to a first profiled wall, and downstream to a second profiled wall, the first profiled wall being arranged upstream from the fins and configured to guide and slow down the flow of air entering the heat exchanger through the fins, and the second profiled wall being arranged downstream from the fins and configured so as to accelerate the flow of air leaving the heat exchanger, wherein the cover has an at least partially curvilinear aerodynamic profile and an outer peripheral surface having surface continuity with radially outer surfaces of the first and second walls.

Optimised heat exchange system of a turbomachine

A fuel supply circuit for an aeronautical cryogenic turbomachine including: at least one cryogenic reservoir containing a liquid fuel topped with a boil-off gas and including a high-pressure liquid pump to supply at least one main propulsion device of the turbomachine with liquid fuel, an auxiliary turbomachine including an electric generator, a gas compressor to supply the auxiliary turbomachine with gaseous fuel, and a buffer gas reservoir connecting the gas compressor to the cryogenic reservoir to reinject gas into the cryogenic reservoir in order to maintain the pressure in the cryogenic reservoir above a predefined value, the electric generator supplying the high-pressure liquid pump and the gas compressor.

Circuit for supplying fuel to an aeronautical cryogenic turbomachine and associated method

A heat exchange system for a turbomachine includes a heat exchanger that has a support wall extending along a longitudinal direction L and a plurality of fins each extending along a radial direction from a radially external surface of the support wall. The heat exchanger further includes a first profiled wall arranged upstream from the fins and configured to guide and slow down the flow of air entering the heat exchanger through the fins. A second profiled wall is arranged downstream from the fins and configured to accelerate the flow of air leaving the heat exchanger. Each first and second profiled wall is attached to the support wall via support elements extending radially from the radially external surface.

Optimized heat exchange system for a turbomachine

A cooling system for cooling a circuit of a first fluid of a turbomachine, the cooling system including a refrigerant fluid circuit including a first heat exchanger for exchanging heat between the refrigerant fluid and air, a second heat exchanger for exchanging heat between the refrigerant fluid and the first fluid, an expander located downstream from the first heat exchanger and upstream from the second heat exchanger in the flow direction of the refrigerant fluid, and a compressor located downstream from the second heat exchanger and upstream from the first heat exchanger; the cooling system further includes a third heat exchanger of the first fluid and air type.

System for cooling a circuit of a first fluid of a turbomachine

A reversible system for dissipating heat power generated in a gas turbine engine, the system including a condenser-forming first heat exchanger, an evaporator-forming second heat exchanger, a scroll compressor suitable for operating as a compressor when the temperature of the cold source is higher than a predefined threshold temperature and as a turbine when the temperature of the cold source is lower than the threshold temperature, an expander and a pump arranged in parallel, and a control valve arranged upstream from the expander and the pump and suitable for directing the refrigerant fluid to the expander when the temperature of the cold source is higher than the threshold temperature and to the pump when the temperature of the cold source is lower than the threshold temperature.

Growing community of inventors

Moissy-Cramayel, France

Samer Maalouf