The Experts below are selected from a list of 309 Experts worldwide ranked by ideXlab platform
Serge Marcel Meunier - One of the best experts on this subject based on the ideXlab platform.
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gas turbine engine Combustion Chamber with oxidizer intake flow control
1992Co-Authors: Gérard Yves Georges Barbier, Xavier Marie Henri Bardey, Serge Marcel MeunierAbstract:An oxidizer intake flow control system is disclosed for a gas turbine engine Combustion Chamber. The Chamber has an oxidizer intake assembly which extends through the wall of the Chamber such that an inlet aperture of the oxidizer intake and an exhaust aperture of the oxidizer intake are located on opposite sides of the wall defining the Combustion Chamber. An oxidizer intake sleeve defines a central passage through which oxidizer may pass into the Combustion Chamber. The intake passage extends along a central axis and the intake assembly is attached to the wall of the Combustion Chamber such that it is rotatable about this central axis. The inlet aperture and/or the exhaust aperture is located in a plane extending non-perpendicularly to the central axis. The Combustion Chamber may have several oxidizer intake assemblies extending through the Combustion Chamber walls. The intake assemblies may be interconnected such that they may be simultaneously rotated with respect to the Combustion Chamber wall.
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low pollution Combustion Chamber for a turbojet engine
1992Co-Authors: Gérard Yves Georges Barbier, M. Bardey H. Xavier, Serge Marcel MeunierAbstract:A low pollution Combustion Chamber for a turbojet engine is disclosed in which first and second Combustion Chambers are oriented in a counter-flow direction and both Combustion Chambers communicate with a separate and distinct exhaust Chamber. The first Combustion Chamber has a fuel injector, as well as a primary oxidizer intake, and the wall bounding the first Combustion Chamber defines a plurality of dilution oxidizer intake orifices. The wall also defines a first exhaust orifice located approximately midway between the upstream and downstream ends of the first Combustion Chamber. A second Combustion Chamber has a second fuel injector, as well as a second primary oxidizer intake, but the wall defining the second Combustion Chamber does not define any dilution oxidizer intake orifices. A second exhaust orifice also communicates with the exhaust Chamber. The orientations of the first and second Combustion Chambers are such that the fuel/oxidizer mixtures traveling through the Combustion Chambers travel in a generally counterflow arrangement. A separate exhaust Chamber is included in the Combustion Chamber assembly and communicates with the first and second Combustion Chambers such that the burned gases from these Chambers enter the exhaust Chamber. The exhaust Chamber defines a third exhaust orifice through which the burned gases exit the Combustion Chamber assembly. The exhaust Chamber is oriented such that the exhaust gases passing through this exhaust Chamber travel in a direction generally parallel to the gases traveling through the second Combustion Chamber. A wall defining the Combustion Chamber defines a second plurality of dilution oxidizer intake orifices so that oxidizer may dilute the exhaust gases passing through this Chamber.
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variable volume Combustion Chamber for a gas turbine engine
1992Co-Authors: Xavier Marie Henri Bardey, Serge Marcel MeunierAbstract:A variable volume Combustion Chamber for a gas turbine engine that has a able wall to vary the volume of the Combustion Chamber. The movable wall is positioned according to the operating conditions of the gas turbine engine, achieving one extreme position under idle power and another extreme position under full power. The movement of the wall between the two extreme positions maximizes the efficiency of the Combustion Chamber for operating conditions between idle and full power. The Combustion Chamber also restricts at least a portion of the oxidizer intake when the movable wall is positioned for idle power conditions and opens the oxidizer intake when the wall is positioned for maximum power conditions to maximize the flow of oxidizer into the Combustion Chamber.
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gas turbine Combustion Chamber with adjustable wall
1992Co-Authors: Xavier Marie Henri Bardey, Serge Marcel MeunierAbstract:The invention relates to a Combustion Chamber comprising a wall (1-6) delimiting it internally and an inlet orifice for primary oxidiser, which establishes communication between the said Combustion Chamber and the general upstream inlet (19) for oxidiser. According to the invention, a part (8) of the wall is adjustable and is coupled to a device (22-24) for setting its adjustment, in such a way as to be able to modify the value of the volume (13) of the Combustion Chamber, this volume having a first value, during operation of the Combustion Chamber at low power, and having a second value, which is less than the said first value, during operation of the Combustion Chamber at full power. One application is the production of a low-pollution gas turbine.
Jakeer Hussain - One of the best experts on this subject based on the ideXlab platform.
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Design and Analysis of C.I. Engine Combustion Chamber Using Cfd
International Journal of Research, 2018Co-Authors: Gopi Kuncham, Jakeer HussainAbstract:fuel turbines besides that the name is commonly carried out to reciprocating inner Combustion (I.C.) engines like the ones determined in everyday automobiles. There are basically sorts of I.C. Ignition engines, those which need a spark plug, and those that rely upon compression of a liquid. Spark ignition engines take a aggregate of fuel and air, compress it, and ignite it the usage of a Chambers. f, the Combustion Chamber model is designed spark plug. In this work an attempt is made to analyse two types of Combustion Chambers. The base line Combustion Chamber is compared with the modified Combustion Chamber. For design of Combustion Chamber Creo software is used and for the analysis part ANSYS CFD is used. The performance and emission parameters like pressure, velocity, mass fraction of O 2 , mass fraction of N 2 and heat transfer coefficient are determined. The obtained results of modified Combustion Chamber are optimum.
Xavier Marie Henri Bardey - One of the best experts on this subject based on the ideXlab platform.
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Combustion Chamber with axially displaced fuel injectors
1993Co-Authors: Gérard Yves Georges Barbier, Xavier Marie Henri BardeyAbstract:A generally annular Combustion Chamber for a gas turbine engine is disclosed in which a plurality of generally cylindrical walls extend forwardly from an upstream end wall of the Combustion Chamber such that each cylindrical wall defines a cavity which is in communication with the interior of the Combustion Chamber. A first fuel injection head is located in each of the cylindrical walls so as to inject fuel into the cavity which is mixed with air and passes into the Combustion Chamber. The first fuel injection heads are located at a first axial position with respect to a longitudinal axis passing through the Combustion Chamber. A plurality of second fuel injection heads are located adjacent to the upstream end wall of the Combustion Chamber so as to spray fuel directly into the Combustion Chamber. The second fuel injection heads are located axially downstream of the axial positions of the first fuel injection heads.
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Combustion Chamber wall
1993Co-Authors: Gérard Yves Georges Barbier, Xavier Marie Henri Bardey, Eric LancelotAbstract:Abstract of EP0565442The invention relates to a Combustion Chamber comprising a pre-mixing Chamber. According to the invention, the walls of this pre-mixing Chamber comprise cells (26), the face of which delimiting the pre-mixing zone is made of a first material which is resistant to a maximum operating temperature, and which cells are filled with a second material, the melting temperature of which is comprised between normal and maximum operating temperatures, and the latent melting heat is greater than 400 kilojoule/kilogramme mass. One application is the production of a Combustion Chamber comprising injectors for the idling and full-gas operating states.
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gas turbine engine Combustion Chamber with oxidizer intake flow control
1992Co-Authors: Gérard Yves Georges Barbier, Xavier Marie Henri Bardey, Serge Marcel MeunierAbstract:An oxidizer intake flow control system is disclosed for a gas turbine engine Combustion Chamber. The Chamber has an oxidizer intake assembly which extends through the wall of the Chamber such that an inlet aperture of the oxidizer intake and an exhaust aperture of the oxidizer intake are located on opposite sides of the wall defining the Combustion Chamber. An oxidizer intake sleeve defines a central passage through which oxidizer may pass into the Combustion Chamber. The intake passage extends along a central axis and the intake assembly is attached to the wall of the Combustion Chamber such that it is rotatable about this central axis. The inlet aperture and/or the exhaust aperture is located in a plane extending non-perpendicularly to the central axis. The Combustion Chamber may have several oxidizer intake assemblies extending through the Combustion Chamber walls. The intake assemblies may be interconnected such that they may be simultaneously rotated with respect to the Combustion Chamber wall.
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flexible wall Combustion Chamber notably for a gas turbine
1992Co-Authors: Xavier Marie Henri Bardey, Serge MeunierAbstract:BREVET D'INVENTION PATENT Chambre de Combustion, notamment pour turbine a gaz, a paroi deformable. Combustion Chamber, particularly for a gas turbine, with deformable wall. ABREGE ABSTRACT L'invention est relative a une chambre de Combustion comprenant une parci (1-6) la delimitant interieurement et un orifice d'admission de comburant primaire, qui etablit une communication entre ladite chambre de Combustion et une admission generale amont (19) de comburant. The invention relates to a Combustion Chamber comprising a PARCI (1-6) delimiting the inside and a primary oxidant inlet port which provides communication between said Combustion Chamber and an upstream general inlet (19) of oxidant . Selon l'invention, une partie (8) de la paroi est deformable et est attelee a un dispositif (22-24) de reglage de sa deformation, de maniere a pouvoir modifier la valeur du volume (13) de la chambre de Combustion, ce volume ayant une premiere valeur, lors du fonctionnement de la chambre de Combustion a According to the invention, a portion (8) of the wall is deformable and is coupled to a device (22-24) for adjusting its deformation, so as to change the volume value (13) of the Combustion Chamber, this volume having a first value, during operation of the Combustion Chamber faible puissance, et ayant une deuxieme valeur, qui est inferieure a ladite premiere valeur, lors du fonctionnement de la chambre de Combustion a pleine puissance. low power, and having a second value, which is lower than said first value, when operating at full power Combustion Chamber. Une application est la realisation d'une turbine a gaz peu pol-luante. One application is the realization of a bit-pol luante gas turbine.
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variable volume Combustion Chamber for a gas turbine engine
1992Co-Authors: Xavier Marie Henri Bardey, Serge Marcel MeunierAbstract:A variable volume Combustion Chamber for a gas turbine engine that has a able wall to vary the volume of the Combustion Chamber. The movable wall is positioned according to the operating conditions of the gas turbine engine, achieving one extreme position under idle power and another extreme position under full power. The movement of the wall between the two extreme positions maximizes the efficiency of the Combustion Chamber for operating conditions between idle and full power. The Combustion Chamber also restricts at least a portion of the oxidizer intake when the movable wall is positioned for idle power conditions and opens the oxidizer intake when the wall is positioned for maximum power conditions to maximize the flow of oxidizer into the Combustion Chamber.
Gopi Kuncham - One of the best experts on this subject based on the ideXlab platform.
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Design and Analysis of C.I. Engine Combustion Chamber Using Cfd
International Journal of Research, 2018Co-Authors: Gopi Kuncham, Jakeer HussainAbstract:fuel turbines besides that the name is commonly carried out to reciprocating inner Combustion (I.C.) engines like the ones determined in everyday automobiles. There are basically sorts of I.C. Ignition engines, those which need a spark plug, and those that rely upon compression of a liquid. Spark ignition engines take a aggregate of fuel and air, compress it, and ignite it the usage of a Chambers. f, the Combustion Chamber model is designed spark plug. In this work an attempt is made to analyse two types of Combustion Chambers. The base line Combustion Chamber is compared with the modified Combustion Chamber. For design of Combustion Chamber Creo software is used and for the analysis part ANSYS CFD is used. The performance and emission parameters like pressure, velocity, mass fraction of O 2 , mass fraction of N 2 and heat transfer coefficient are determined. The obtained results of modified Combustion Chamber are optimum.
A. M. Tsyganov - One of the best experts on this subject based on the ideXlab platform.
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The generalized characteristic of the Combustion Chamber for a gas-turbine engine
Thermal Engineering, 1999Co-Authors: Yu. L. Kovylov, S. V. Krasheninnikov, S. V. Lukachev, A. M. TsyganovAbstract:Aspects describing the operation of a gas-turbine Combustion Chamber by a set of similarity parameters are considered. The concept of the generalized Combustion-Chamber characteristic is introduced, and the system of coordinates for the field containing the generalized Combustion-Chamber characteristic is substantiated.