Societe Nationale D'etude Et De Construction De Moteurs D'aviation

Jean-Paul D Alary

Denis J Sandelis

Michel A Desaulty

Pierre M Schroer

Christophe Pieussergues

Denis R Ansart

Gerard Y Barbier

Guy D'Agostino

Henry Roger Leclerc

Didier Merville

Francois J Mirville

Bruno R Masse

Jacques G Havard

Serge R Muccioli

Paul Mackovic

Corine G Delahaye

Stephane Jean-Marie Courtet

Joe L Jamet

Yves Francois Salan

Ralph M Stelter

An annular combustion chamber is disclosed for use in a gas turbine engine, the combustion chamber having an axis of symmetry, an inner annular wall, an outer annular wall, and a forward end extending between the inner and outer wall to form boundaries for the combustion chamber. The forward end of the combustion chamber has an inner ring member extending about the axis of symmetry and an outer ring member extending about the axis of symmetry and radially spaced from the inner ring member, the inner and outer ring members forming inner and outer boundaries of an annular chamber that diverges in a rearward direction. The inner and outer ring members are interconnected by a plurality of circumferentially spaced apart spacers so as to form a plurality of arcuate openings between adjacent spacers. A plurality of fuel injector assemblies are associated with the forward end of the combustion chamber, each fuel injector assembly comprising an arcuate injection manifold located in an arcuate member, in turn, located in one of the plurality of arcuate openings so as to divide the arcuate opening into an inner annular space and an outer annular space, the injection manifold having an inner array of injection orifices to inject fuel into the inner annular space, and an outer array of injection orifices to inject fuel into the outer annular space. The inner and outer ring members have a plurality of air swirlers located forwardly of the fuel injection orifices to direct air flows into the inner and outer annular spaces in counter-rotation directions around the axis of symmetry. The injection orifices are oriented so as to direct fuel into the inner and outer annular spaces generally in the same direction as the air flow in the respective annular space.

Reduced pollution combustion chamber having an annular fuel injector

An improved dual-head combustion chamber is disclosed having a generally annular configuration extending about a central axis with a low power head, operating during low power engine conditions and a radially displaced high power head operative under high power engine operating conditions. The low power head has N number of fuel/air injector assemblies arranged in an annular array and spaced apart in a circumferential direction about the central axis. The fuel/air injector assemblies of the low power head have an air permeability of P1. The high power head also is arranged in a generally annular array with N number of first fuel/air injector assemblies and N number of second fuel/air injector assemblies with each of the second fuel/air injector assemblies aligned with a fuel/air injector assembly of the low power head along a radius line extending from the central axis. The second fuel/air injector assemblies have an air permeability of P2 such that P2 is greater than P1 and supply a fuel/air mixture to the combustion chamber during high power operation. The first fuel/air injector assemblies located in the high power head are located circumferentially spaced between adjacent second fuel/air injector assemblies. The first fuel/air injector assemblies have an air permeability of P1 and supply fuel/air mixture to the combustion chamber during low power operation.

Dual head combustion chamber

A diffuser for a turbojet engine is disclosed in which a plurality of diffuser inlets are arranged in a substantially circular array bounded by inner and outer diffuser walls and by a plurality of partitions extending generally radially from the axis of the annular diffuser. The plurality of diffuser inlets are located so as to receive air or oxidizer from the turbojet engine compressor and the radial partitions may be integrated into the compressor guide vanes. The diffuser has a plurality of sets of diffuser outlets, each set comprising a plurality of diffuser outlets arranged in a circular array about the central axis of the diffuser. The radius of each set of diffuser outlets is different from the radius of each of the other sets of diffuser outlets such that the entirety of diffuser outlets comprise a non-circular array. The diffuser may comprise three different sets of diffuser outlets, a first set directing air or oxidizer onto the baffle such that the air or oxidizer passes through openings in the baffle to feed the fuel injector heads. A second set of diffuser outlets may be curved outward at the outlet end so as to direct a portion of the air or oxidizer into the space defined between the outer combustion chamber wail and the outer casing. A third set of diffuser outlets may be curved inwardly at their downstream ends so as to direct a portion of the air or oxidizer into the space between the inner combustion and the inner casing.

Gas turbine diffuser

A separator-diffuser for a gas turbine engine is disclosed wherein the diffuser includes axial walls which function as a guide vane stage for the oxidizer compressor. By incorporating the last, or downstream, guide vane stage into the diffuser structure, the overall axial length and bulk of the gas turbine engine may be significantly reduced. The separator-diffuser has a wall defining a generally annular oxidizer flow passage extending around the central axis of the gas turbine engine, the passage having an oxidizer inlet located downstream of the last rotor stage of the oxidizer compressor so as to enable the oxidizer to pass from the oxidizer compressor into the oxidizer flow passage. A generally annular separator member is located in the oxidizer flow passage downstream of the oxidizer inlet so as to divide the oxidizer flow passage into at least two separate oxidizer flow paths, each flow path having a separate oxidizer outlet. The oxidizer outlets are positioned so as to direct the oxidizer towards one of the annular array of fuel injection heads. A plurality of circumferentially spaced apart, axially extending primary arms connect the separator member to the diffuser walls so as to support the separator within the oxidizer passageway and to serve as a guide vane stage for the oxidizer emanating from the oxidizer compressor.

Gas turbine engine having an integral guide vane and separator diffuser

The present invention relates to a system for cooling a high power fuel injector of a dual fuel injector wherein the system comprises a first fuel supply circuit having a first conduit connecting a fuel feed supply and the high power fuel injector, the first conduit having a terminal end adjacent to a distal end of the high power fuel injector, and a second conduit connecting the terminal end of the first conduit to the low power fuel injector such that all of the fuel supplied to the low power injector first passes through the high power fuel injector. The system also has a second fuel supply circuit, separate from the first fuel supply circuit, which comprises a third conduit connecting the fuel feed supply and the fuel injection orifices of the high power fuel injector so as to supply fuel to the fuel injection orifices.

System for cooling a high power fuel injector of a dual injector

The present invention relates to a method and apparatus for supplying fuel to and cooling a fuel injector of a gas turbine engine having a dual head combustion chamber. The method comprises the steps of supplying a total fuel flow to the fuel injector such that at least a portion of the total fuel flow circulates through the high power injector nozzle during all operational modes of the gas turbine engine, including those modes in which the high power injector is not supplying fuel to the combustion chamber, and evacuating unused fuel from the high power injector. The apparatus includes a fuel supply conduit connected to the high power injector to supply at least a portion of the total fuel flow supplied to the fuel injector to the high power injector during all operational modes of the gas turbine engine; a fuel control valve to control the amount of fuel flowing through the fuel injector orifices; and a fuel evacuation conduit connected to the high power injector so as to evacuate unused fuel from the high power injector.

System for supplying fuel to and cooling a fuel injector of a dual head

A gas flow separator for an annular combustion chamber of a gas turbine engine is disclosed in which the radially spaced apart first and second gas flow separator walls which extend axially into the combustion chamber from the combustion chamber upstream end wall each define a plurality of axially extending channels. Each of the channels extends generally axially in an upstream direction from the downstream edge of each of the separator walls such that their axial lengths are less than the axial lengths of the respective separator walls. Both the depth and the width of each of the channels increases from its upstream end point to the downstream edges of the separator walls. The channels may be circumferentially aligned with each other, or the channels of one separator wall may be circumferentially offset from the channels of the other separator wall.

Gas-flow separator for a double dome gas turbine engine combustion

A separator for an annular gas turbine engine combustion chamber is disclosed having a plurality of separator segments arranged in a generally annular configuration to form an annular separator extending from an upstream end wall of a combustion chamber into the combustion chamber so as to separate first and second combustion zones within the combustion chamber. Each of the separator segments has a hollow interior defined by a front wall, an outer wall, an inner wall which has at least a portion tapering or converging towards the outer wall in a direction extending away from the front wall, and first and second sides. The sides define an array of holes communicating with the hollow interior, the positioning of the array of holes on a first sides being different from that of the array of holes on the second sides such that the axes of the holes are out of alignment with each other. The first sides of one separator segment is positioned adjacent to, but spaced apart from a second sides of an adjacent separator segment. Since the array of holes on the first sides is out of alignment with the array of holes on the second sides, pressurized gas within the interior of the hollow segment will pass through the holes in the first and second sides and will impinge upon the adjacent sides so as to cool both the adjacent sides and the sides through which the gas passes.

Growing community of inventors

Saint Maur des Fosses, France

Jean-Paul D Alary