Abstract: A vane adjustment mechanism, for controlling the quantity of exhaust gas including a base unit having an inner base unit and an outer base unit. The inner base unit (2A) has first and second flanges, and is forced into the outer base unit (2B). A plurality of U-shaped indentations (2c) are spaced at regular angular intervals and each indentation extends from the first flange (2a) to the second flange (2b), so that the U-shaped indentations form vane shaft holes for accommodating the vane lever units (3) when the inner base unit is inserted into the outer base unit to block the U-shaped indentations in such a way that the vane lever units are free to rotate. A link plate (4) has U-shaped indentations, in which protrusions of the vane lever units (3) engage, all along the circumferential edge of the link plate.

Abstract: STATOR VANE BLANK AND METHOD OF FORMING THE VANE BLANK A forged vane blank for forming a stator vane for a rotary machine is disclosed. Various construction details are developed which facilitate forging and machining of the vane blank into its final form as a stator vane. In one detailed embodiment, the vane blank has a greater draft angle at the outer surface than the draft angle at the inner surface as a result of the forging operation.

Abstract: An annular turbine frame has ring disposed coaxially about an axial centerline axis and includes a plurality of circumferentially spaced apart ports. A plurality of circumferentially spaced apart struts are joined radially to the ring by devises on the ring. Each strut has radially opposite first and second ends, and a through channel extending therebetween. Each of the channels is aligned with a corresponding one of the ports. Each of the ports has a port counterbore though a radially outer portion of the port forming a shoulder in the port. A seal is disposed within the port counterbore between the shoulder and the strut.

Abstract: A worked nozzle ring for a gas turbine, in particular an aircraft engine, having at least one shroud and at least one blade sheet arranged thereon, whereby, in order to create a worked nozzle ring that is easy to manufacture, the blade sheet comprises, at the frontal side, at least one two-dimensionally profiled connecting space region that is placed in a profiled opening formed in the shroud by beam cutting and is connected therewith.

Abstract: A reversible nozzle (10), removably attached to a fluid emitting base, such as a half turbine casing (22). The reversible nozzle (10) has a nozzle body (16) and a nozzle tube (12), with the nozzle body (16) preferably forming a plurality of fastener receiving slots (18, 18a). The nozzle tube (12) is angled with respect to the nozzle body (16). An installed reversible nozzle (10) is reversed by removing fasteners (34) connecting the nozzle body (16) to the fluid emitting base (22), rotating the nozzle body (16) about a normal nozzle body axis X, and resecuring the reversible nozzle (10) to the fluid emitting base (22) with fasteners (34). To aid in the alignment of the reversible nozzle (10), one fastener receiving slot (18a) is preferably elongated.

Abstract: A stator assembly for a rotary machine having a shroud for a stator vane is disclosed. Various construction details are developed which limit movement of the stator vane into the flowpath by reason of the stator vane being restrained by the shroud. In one particular embodiment, a clip member extends through an opening in the tip of the vane and is disposed at a location adjacent a nonflowpath surface of the shroud to restrain the tip of the vane against inward movement through the shroud.

Abstract: A support and locking device for nozzles of a high-pressure stage in gas turbines comprises a plurality of groups of stator vanes, which are associated with a plurality of outer sealing plates, for connection of the groups to the outer liner of the combustion chamber, and are associated with a plurality of inner sealing plates, for connection of the groups to the inner liner of the combustion chamber. Each of the groups of stator vanes is locked by an inner ring, and the ring has a first series of outer holes to reinforce this locking, and a second series, of inner, through holes, which are provided in an inner extension of the ring and are used to secure the ring itself to the structure of the gas turbine.

Abstract: A network switch for network communications includes at least one data port interface supporting a plurality of data ports transmitting and receiving data. A CPU interface is configured to communicate with a CPU, and an internal memory communicates with the at least one data port interface. A memory management unit is provided for communicating data from at least one data port interface and the memory. A communication channel is provided, for communicating data and messaging information between the at least one data port interface, the memory, and the memory management unit. The configuration of the network switch also includes a fast filtering process, with the fast filtering processor filtering packets coming into the at least one data port interface. Selective filter action is taken based upon a filtering result.

Abstract: The variable-capacity turbine according to this invention is provided with a nozzle adjustment mechanism, having a nozzle drive components, a lever and nozzle vane, would all be housed at the inner side of the scroll in the turbine casing. This would reduce the axial length of the turbine and make it more compact, and thus easier to install in a car. It would also avoid the problem of the center casing becoming too complex. There would be fewer assembly and disassembly processes, and the turbine would be easier for maintenance. This variable-capacity turbine has nozzle drive members for the nozzles which is connected to an actuator that causes the drives member to rotate around the shaft turbine; and a nozzle adjustment mechanism which includes a number of connectors to link the nozzle drive members to the nozzle vanes.

Abstract: A two stage jointed stationary blade of a high pressure or intermediate pressure steam turbine is formed with a bolt joint in place of a welded joint so as to make detachment and disassembly possible, and thereby facilitating maintenance and inspection work and reducing assembling man-hours. A stationary blade (front stage)(2), outer ring front portion (1) and inner ring front portion (3) are welded into an integral structure. A stationary blade (rear stage) 22, outer ring rear portion (21) and inner ring rear portion (23) are also welded into an integral structure. The outer ring front portion 1, outer ring center portion 10 and the outer ring rear portion 21 are mutually engaged via engaging portions (4, 11 and 12, 24) with precise positioning and then jointed together integrally by bolt (30).

Abstract: A seating spring is provided for a gas turbine engine compressor stator having a casing with a circumferential casing slot for mounting a plurality of vane sectors at outer bands thereof. The seating spring has at least one reaction tab configured to abut the casing at one side of the casing slot and a spring arm connected to the reaction tab and configured to abut a respective one of the outer bands to bias the outer band against the casing at a second side of the casing slot. A retention arm is connected to the reaction tab and engages the casing so as to be prevented from moving radially outward. The spring arm is thereby retained in contact with the outer band.

Abstract: A ceramic nozzle for a gas turbine stage of a turbomachine (e.g., a turbopump) includes a splined mounting surface. Ceramic splines on the nozzle mounting surface are interlocked with metal mating splines on a surface of a turbine housing to prevent the nozzle from rotating relative to the housing. Both sets of splines extend in a radial direction, are straight and have trapezoidal shapes in transverse cross-section. These splines maintain a constant contact angle during large temperature excursions, when inherent thermal growth mismatches between ceramic and metal occur.

Abstract: A vane element adapted for assembly with a plurality of further vane elements to form a ring of vanes for a low pressure gas turbine. Each vane element has a vane blade with platforms at its outer and inner ends, the platform at the outer end being adapted for connection to a housing. Each platform has a flange integral with the vane blade and an outer wall spaced radially from the flange and joined thereto by a radial wall having a lateral projection. Opposite the projection, a recess is formed between the flange and the outer wall, the recess having a shape corresponding to that of the projection so that a plurality of the vane elements can be assembled to form the vane ring by engaging the projection of one vane element in the recess of an adjacent vane element. The projections are form-fit in the recesses so that the platforms of the vane elements are flush with one another.

Abstract: A turbine nozzle includes ceramic outer and inner bands, with a ceramic vane forward segment integrally joined thereto. A ceramic vane aft segment has opposite ends trapped in complementary sockets in the bands.

Abstract: Apparatus and method for directing a flow of fluid to a turbine via a nozzle box mountable to encircle a shaft. The nozzle box includes a housing having an inner wall spaced from an outer wall and joined therewith so as to form a chamber therein. The housing also includes at least one inlet and at least one outlet in which each is in fluid flow communication with the chamber. A plurality of radially projecting nozzles are positioned between the inner and outer walls and located upstream of the outlet for directing the flow of fluid through the outlet. A flow distributor is positioned between the inner and outer walls and located upstream of the nozzles for directing the flow of fluid through the chamber and to the nozzles. The flow distributor is configured to obtain a substantially uniform flow of fluid to the nozzles.

Abstract: A turbine nozzle includes a plurality of vanes joined at opposite ends to outer and inner bands. The inner band has a forward hook which is segmented to reduce thermal mismatch. And, in additional embodiments the vane includes an impingement baffle having preferential cooling.