Abstract: The present invention relates to a turbine engine casing (1), in particular a turbojet exhaust casing, including at least one hoop (2) and at least one flange (3, 4) at least partially defining one end of said hoop (2), and at least one cap (5) positioned at least partially on the outer surface of the hoop (2), said cap (5) including a bore (6) capable of receiving an element for fastening the casing (1) to a bracket, the flange including an access cut-out (7a) substantially coaxial with the bore (6) of said at least one cap (5), said access cut-out (7a) enabling access to the bore (6), the access cut-out (7a) being provided at a release cut-out (7b) which is wider than the flange (3, 4) and constitutes a recess on said release cut-out (7b). The invention also relates to a turbine engine including a casing (1) and to a method for machining the latter according to the present invention.

Abstract: PNA is a synthetic molecule analogue to DNA that, due to its physicochemical properties, allows a faster analysis with higher sensitivity and specificity than the DNA probes. These probes are combined with fluorescence in situ hybridization (FISH), a molecular biology technique that allows the direct visualization of the microorganisms in the sample. The combination of these two technologies rendered the FISH procedure to be faster, simpler and more efficient. This method can be applied to a great variety of samples such as food, blood, biopsies, feces, water and other clinical, environmental or agriculture and food industry samples. The present invention also includes the development of the kit of detection and respective procedure for the specific identification of Escherichia coli O157:H7 using the above referred sample types.

Abstract: The present invention relates to a turbine engine casing (1), in particular a turbojet exhaust casing, including at least one hoop (2) and at least one flange (3, 4) at least partially defining one end of said hoop (2), and at least one cap (5) positioned at least partially on the outer surface of the hoop (2), said cap (5) including a bore (6) capable of receiving an element for fastening the casing (1) to a bracket, the flange including an access cut-out (7a) substantially coaxial with the bore (6) of said at least one cap (5), said access cut-out (7a) enabling access to the bore (6), the access cut-out (7a) being provided at a release cut-out (7b) which is wider than the flange (3, 4) and constitutes a recess on said release cut-out (7b). The invention also relates to a turbine engine including a casing (1) and to a method for machining the latter according to the present invention.

Abstract: A method is described for controlling instability of operation in a de-ethanizer tower (13) in the gas recovery unit in fluid catalytic cracking units and delayed coking units. The method comprises the step of intervening in the de-ethanizer tower (13) when instability occurs in it, and adjusting the material balance of water in such a way that the excess of water in the feed load stream (9) is removed only as an azeotrope. The intervention is performed by introducing into the feed load stream (9) of the de-ethanizer tower (13) a volume fraction (18) of a flow of hydrocarbon, which may be either dry hydrocarbons or hydrocarbons with a low level of water content.

Abstract: A method is described for controlling instability of operation in a de-ethanizer tower (13) in the gas recovery unit in fluid catalytic cracking units and delayed coking units. The method comprises the step of intervening in the de-ethanizer tower (13) when instability occurs in it, and adjusting the material balance of water in such a way that the excess of water in the feed load stream (9) is removed only as an azeotrope. The intervention is performed by introducing into the feed load stream (9) of the de-ethanizer tower (13) a volume fraction (18) of a flow of hydrocarbon, which may be either dry hydrocarbons or hydrocarbons with a low level of water content.

Abstract: The invention concerns a turbine engine annular combustion chamber, comprising longitudinal walls (6, 8) connected by a transverse chamber bottom (10) and a single-piece cowling (12), the chamber bottom (10) and the cowling (12) each comprising an inner flange (16, 20) and an outer flange (18, 22) each with a plurality of holes made in it for the passage of fixing systems (14a, 14b) for fixing the cowling on the chamber bottom. Each fixing system has associated with it at least one tangential slot (30) formed on the corresponding flange (16, 18) of the chamber bottom (10) and/or on the corresponding flange (20, 22) of the cowling (12), each slot (30) being formed in the immediate vicinity of the corresponding fixing system (14a, 14b).

Abstract: The gas turbine comprises an annular combustion chamber having inner and outer walls made of ceramic matrix composite material, and a high pressure turbine nozzle secured to a downstream end of the combustion chamber and comprising a plurality of stationary airfoils extending between the inner and outer walls of an annular flow path through the nozzle for the gas stream coming from the combustion chamber. The turbine nozzle is made of ceramic matrix composite material and it is connected to the downstream end of the combustion chamber by brazing.

Abstract: The high pressure turbine nozzle is mechanically connected to a downstream end portion of the combustion chamber and inner and outer connection ferrules connect the combustion chamber and turbine nozzle assembly to inner and outer metal shrouds in order to hold said assembly between the shrouds. Locking members are provided to prevent the turbine nozzle from turning about its axis relative to at least one of the metal shrouds so as to prevent the forces that are exerted on the turbine nozzle vanes by the flow of gas coming from the chamber being taken up by the portions of the connection ferrules that extend between the combustion chamber and turbine nozzle assembly and the metal shrouds.

Abstract: The downstream end portions of the inner and outer walls of the combustion chamber of the gas turbine are pressed against the inner and outer platforms respectively of the vanes of the high pressure turbine nozzle and they extend thereover substantially to the downstream end of the platforms, and the means for mechanically connecting the turbine nozzle to the downstream end portions of the combustion chamber walls are formed by connection screws implanted in the airfoils of the vanes of the turbine nozzle, passing through holes formed in the end portions of the combustion chamber walls. Thus, the downstream end portions of the combustion chamber walls contribute to preventing leakage from the gas stream at the interface between the chamber and the nozzle, and also along the nozzle.

Abstract: The annular combustion chamber having ceramic matrix composite material walls is mounted inside a metal casing by linking members fastened to the chamber by brazing. The linking members comprise a plurality of inner linking tabs and a plurality of outer linking tabs connecting the chamber to the inner and outer metal shrouds of the casing, each linking tab has a first portion fastened to the outside surface of a wall of the combustion chamber by brazing, the first portions of the linking tabs being spaced apart from one another circumferentially so that the brazed connections between the chamber and the linking members occupy a set of limited zones that are spaced apart from one another.

Abstract: An annular combustion chamber comprising axial walls interconnected by a chamber end wall having a coefficient of thermal expansion that is different from that of the axial walls, the chamber end wall being provided with a plurality of inner and outer fastener tabs secured by fastener systems to the end portions of the axial walls. Each fastener system comprises a bolt, a nut tightened onto one of the ends of the bolt, and a slideway bushing disposed around the bolt between the nut and the end portion of the corresponding axial wall, a determined amount of radial clearance being provided between the nut and the end portion of the axial wall so as to enable the chamber end wall to expand radially freely in operation relative to the axial walls.

Abstract: The invention provides a combustion chamber comprising a chamber wall disposed radially inside a casing, an igniter plug for igniting the air-fuel mixture, the plug being mounted on said casing and comprising a body with a free end that is disposed in an opening formed through said chamber wall with a large amount of clearance to accommodate relative displacement between said casing and said chamber wall, and a sealing device provided between said body and the perimeter of said opening, said sealing device comprising an annular plug-guide through which said body passes, the plug-guide being slidably mounted at the radially-outer end of an annular support whose base is secured to said perimeter, wherein the support is secured to the radially-outer portion of a chimney passing through said opening and presenting at its radially-inner end a collar bearing against the inside face of the chamber wall, and wherein a cooling circuit for said collar is provided.

Abstract: The invention relates to an annular combustion chamber for a turbomachine of axis X, in which the chamber end wall is fixed to inner and outer side walls by means of a plurality of radially-inner attachment fittings and by means of a plurality of radially-outer attachment fittings disposed upstream from said chamber end wall by bolting a zone of each of said fittings to said side walls. At least one of said pluralities of attachment fittings is integrated in a ring secured to the chamber end wall and comprises a plurality of pairs of tabs which extend upstream beyond the bolting zones, the two tabs in each pair being disposed circumferentially on either side of a bolting zone and being interconnected at their upstream end to the upstream end of a fixing plate which extends between said two tabs and which presents a bolting zone for being fixed to the adjacent side wall.

Abstract: The annular combustion chamber having ceramic matrix composite material walls is mounted inside a metal casing by linking members fastened to the chamber by brazing. The linking members comprise a plurality of inner linking tabs and a plurality of outer linking tabs connecting the chamber to the inner and outer metal shrouds of the casing, each linking tab has a first portion fastened to the outside surface of a wall of the combustion chamber by brazing, the first portions of the linking tabs being spaced apart from one another circumferentially so that the brazed connections between the chamber and the linking members occupy a set of limited zones that are spaced apart from one another.

Abstract: The high pressure turbine nozzle is mechanically connected to a downstream end portion of the combustion chamber and inner and outer connection ferrules connect the combustion chamber and turbine nozzle assembly to inner and outer metal shrouds in order to hold said assembly between the shrouds. Locking members are provided to prevent the turbine nozzle from turning about its axis relative to at least one of the metal shrouds so as to prevent the forces that are exerted on the turbine nozzle vanes by the flow of gas coming from the chamber being taken up by the portions of the connection ferrules that extend between the combustion chamber and turbine nozzle assembly and the metal shrouds.

Abstract: The downstream end portions of the inner and outer walls of the combustion chamber of the gas turbine are pressed against the inner and outer platforms respectively of the vanes of the high pressure turbine nozzle and they extend thereover substantially to the downstream end of the platforms, and the means for mechanically connecting the turbine nozzle to the downstream end portions of the combustion chamber walls are formed by connection screws implanted in the airfoils of the vanes of the turbine nozzle, passing through holes formed in the end portions of the combustion chamber walls. Thus, the downstream end portions of the combustion chamber walls contribute to preventing leakage from the gas stream at the interface between the chamber and the nozzle, and also along the nozzle.

Abstract: The gas turbine comprises an annular combustion chamber having inner and outer walls made of ceramic matrix composite material, and a high pressure turbine nozzle secured to a downstream end of the combustion chamber and comprising a plurality of stationary airfoils extending between the inner and outer walls of an annular flow path through the nozzle for the gas stream coming from the combustion chamber. The turbine nozzle is made of ceramic matrix composite material and it is connected to the downstream end of the combustion chamber by brazing.

Abstract: The invention provides a combustion chamber comprising a chamber wall disposed radially inside a casing, an igniter plug for igniting the air-fuel mixture, the plug being mounted on said casing and comprising a body with a free end that is disposed in an opening formed through said chamber wall with a large amount of clearance to accommodate relative displacement between said casing and said chamber wall, and a sealing device provided between said body and the perimeter of said opening, said sealing device comprising an annular plug-guide through which said body passes, the plug-guide being slidably mounted at the radially-outer end of an annular support whose base is secured to said perimeter, wherein the support is secured to the radially-outer portion of a chimney passing through said opening and presenting at its radially-inner end a collar bearing against the inside face of the chamber wall, and wherein a cooling circuit for said collar is provided.

Abstract: The invention relates to an annular combustion chamber for a turbomachine of axis X, in which the chamber end wall is fixed to inner and outer side walls by means of a plurality of radially-inner attachment fittings and by means of a plurality of radially-outer attachment fittings disposed upstream from said chamber end wall by bolting a zone of each of said fittings to said side walls. At least one of said pluralities of attachment fittings is integrated in a ring secured to the chamber end wall and comprises a plurality of pairs of tabs which extend upstream beyond the bolting zones, the two tabs in each pair being disposed circumferentially on either side of a bolting zone and being interconnected at their upstream end to the upstream end of a fixing plate which extends between said two tabs and which presents a bolting zone for being fixed to the adjacent side wall.