Showing papers by "Alain Dominique Gendraud published in 2005"

Device for tuning clearance in a gas turbine, while balancing air flows

Abstract: A device for tuning clearance at rotor blade tips in a gas turbine rotor, the device comprising at least one annular air flow duct that is mounted around the circumference of an annular casing of a stator of the turbine, the annular air flow duct being designed to discharge air onto the casing in order to modify the temperature thereof. A tubular air manifold is disposed around the air flow duct(s). There are also disposed an air feed tube to supply the tubular air manifold with air and an air pipe opening in the tubular air manifold and opening out into the air flow duct(s). The air pipe is provided with a balancing diaphragm for balancing the air flowing through the pipe.

Stationary ring assembly for a gas turbine

Abstract: A stationary ring assembly forming a rotor shroud for a gas turbine, the stationary ring assembly comprising a plurality of segments having adjacent side faces that are placed end to end with sealing means interposed therebetween, the sealing means comprising at least one axial sealing strip and at least one radial sealing strip respectively received in axial slots and in radial slots formed facing one another in the adjacent side faces of the segments, at least one end of each radial slot opening out into the corresponding axial slot, each axial slot of a segment presenting a depth that is greater than the depth of the corresponding radial slot, and the axial sealing strip presenting a width that is greater than the width of the radial strip.

Gas turbine clearance control devices

Abstract: A clearance control device for controlling clearance between rotary blade tips and a stationary bushing of a gas turbine having a casing that is provided with at least two annular ridges, the clearance control device including a circular tuning unit that includes air circulation means for circulating air, said means being made up of at least three ducts; air supply means for supplying air to the air flow ducts; and air discharge means for discharging air on the ridges in order to modify the temperature, the air discharge means for each duct being made up of at least one top row having a number N of perforations disposed facing one of the side faces of the ridges and of at least one bottom row having a number 2N of perforations disposed facing a connection radius that connects the ridges to the casing.

Dispositif de pilotage de jeu de turbine a gaz a equilibrage des debits d'air

Abstract: Dispositif de pilotage de jeu en sommet d'aubes mobiles d'un rotor de turbine a gaz, comportant au moins une rampe annulaire de circulation d'air (14) montee circonferentiellement sur un carter annulaire (12) d'un stator de la turbine et destinee a decharger de l'air sur ledit carter (12) afin d'en modifier la temperature. Un tube collecteur d'air (20) est dispose autour de la ou des rampes de circulation d'air (14). On dispose egalement un tube d'alimentation en air (22) pour alimenter en air le tube collecteur d'air (20) et une conduite d'air (24) s'ouvrant dans le tube collecteur d'air (20) et debouchant dans la ou les rampes de circulation d'air (14). La conduite d'air (24) est pourvue de moyens (30) pour equilibrer le debit d'air la traversant.

Improved gas turbine clearance control device

Abstract: PROBLEM TO BE SOLVED: To provide a clearance control device for efficiently and uniformly cooling a fixed bushing by optimizing the injection of air. SOLUTION: The clearance control device comprises an annular adjusting unit 26 having an air circulating means for circulating air. The air circulating means includes at least three ducts 28, 30, 32, an air supply means for supplying air to the air flow ducts 28, 30, 32, and an air releasing means for releasing air to protruded portions 18, 20 to change the temperature thereof. The air releasing means for each duct is constituted by at least one upper side train having N-piece through-holes 34 arranged facing one of side faces 18a, 18b, 20a, 20b of the protruded portions 18, 20 and at least one lower side train having 2N-piece through-holes 36 arranged facing connection radial portions 18c, 18d, 20c, 20d connecting the protruded portions 18, 20 to a casing. COPYRIGHT: (C)2005,JPO&NCIPI

Stator of a high-pressure turbine of a turbomachine, and a method of assembling it

Abstract: A method of assembling sectored elements of an annular stator of a high-pressure turbine of a turbomachine about a longitudinal axis of said turbine, in which method an angular distribution pattern is defined for distributing elements of the stator over a predetermined angular sector, said pattern being defined so as to prevent inter-sector zones of stator elements being in radial alignment, said zones being defined between two adjacent sectors of the same stator element, and so as to repeat said distribution pattern around the entire circumference of the stator.

Device for adjusting gap of gas turbine at the same time when balancing air flow

Abstract: PROBLEM TO BE SOLVED: To reduce the non-uniformity of a temperature around the stator of a turbine by balancing an air flow in an adjusting device SOLUTION: This device for adjusting a gap at a rotor blade tip of a gas turbine rotor comprises at least one annular air flow duct 14 mounted around a peripheral portion of an annular casing 12 of the stator of the turbine The annular air flow duct injects air to the casing 12 to change the temperature of the casing A tubular air manifold 20 is arranged around the air flow duct 14 Furthermore, there are arranged an air supply tube 22 for supplying air to the tubular air manifold 20 and an air pipe 24 opened in the tubular air manifold 20 and opened into the air flow duct 14 The air pipe 24 has a means 30 for balancing air flowing through the pipe COPYRIGHT: (C)2005,JPO&NCIPI

Feather seal configuration for a gas turbine shroud

Abstract: The assembly has multiple ring and spacer segments. Axial and radial sealing tongues (42, 44) are respectively housed in an axial slot (36) and a radial slot (38) placed oppositely in adjacent side faces of the segments. The axial slot of each segment has depth higher than depth of the radial slot. The axial tongue has width greater than the width of the radial tongue.

High pressure turbine stator of a turbo-engine and his assembling process

Abstract: The method involves defining an angular distribution pattern of units of a stator (10) on a predetermined angular sector. The pattern is repeated on entire circumference of the stator so that temperature is distributed symmetrically on entire circumference of a casing (12) of the stator. A set of angular sectors of a case (24) is placed around the casing, to discharge air from the casing. The pattern is defined to avoid radial alignment between inter-spacer zones (14a), defined between two adjacent spacers (14), and inter-sector zones (24a) defined between two adjacent sectors of the case (24). An independent claim is also included for a stator of a high-pressure turbine of a turbomachine.

Stator for high pressure turbine of turbo machine and its assembling method

Abstract: PROBLEM TO BE SOLVED: To provide a method for adjusting a blade end gap due to thermal deformation to be minimized. SOLUTION: The method is provided for assembling members 14, 24 parted into sectors of an annular stator 10 for a high pressure turbine of a turbo machine around a vertical axis X-X of the turbine. An angle distributing pattern is specified for distributing stator elements over predetermined angle sectors Ψ. The pattern is specified to prevent the radial arrangement of sector-to-sector regions 14a, 24a of the stator elements 14, 24. The regions are defined between two adjacent sectors of the same stator element. The pattern is specified to repeat the distributed pattern around the whole periphery of the stator. COPYRIGHT: (C)2005,JPO&NCIPI

Stator de turbine haute-pression de turbomachine et procédé d'assemblage

Abstract: Procede d'assemblage d'elements sectorises (14, 24) d'un stator annulaire (10) d'une turbine haute-pression de turbomachine autour d'un axe longitudinal (X-X) de ladite turbine, procede selon lequel, on definit un motif de repartition angulaire des elements du stator pour un secteur angulaire predetermine ( Ψ ), le motif de repartition etant defini de facon a eviter un alignement radial entre des zones inter-secteurs (14a, 24a) des elements du stator (14, 24) definies entre deux secteurs adjacents d'un meme element du stator, et a repeter ledit motif de repartition sur toute la circonference du stator.