Abstract: An improved design for a structure such as a turbine vane or blade subjected to extreme temperature levels and/or gradients resulting in extreme deformation stresses within the structure. The present structures comprise an interior skeletal support having a plurality of spaced, flexible support legs which extend out and are attached to spaced areas of a flexible outer surface skin which is subjected to extreme temperature levels or temperature gradients during use. The extreme stresses normally developed by the expansion of the surface skin are avoided by the ability of the skin to move minutely and flex the spaced support legs to variable extents and in predetermined directions.

Abstract: Apparatus and method for reducing thermal stress in the casings of a steam turbine. A novel inlet sleeve carries high pressure steam from the bell connector of an inlet pipe through the turbine inner casing. The inlet sleeve is connected at a first end to the bell connector and secured at a mid portion to the inner casing so that the second end of the inlet sleeve may terminate adjacent the inner casing wall without contacting the inner casing. This connection means forms a cylindrical chamber having a closed end at the mid portion of the inlet sleeve and an open end adjacent the inner wall of the turbine inner casing. The cylindrical chamber provides a thermal shield which isolates portions of the turbine inner casing adjacent the inlet sleeve from the rapid steam flow between the inlet pipe and the turbine blading.

Abstract: A support of an intank pump at a pump support, which includes webs of elastic material that extend from the pump to the pump support in a direction deviating at an angle .alpha. from the radial which is determined by the longitudinal axis of the fuel pump. During swelling of the webs by the fuel, a rotary movement is thereby imparted to the pump without influencing the suction height. The webs may thereby have a relatively large volume as a result of which a good damping is achieved.

Abstract: A supporting structure comprises a shell and a plurality of support members which are independent of each other, inserted in the shell and arranged so that the flexural rigidity is smaller in the water flow than in a perpendecular to the water flow. The supporting structure supports one place of an axial-flow bulb turbine which is to be supported at two places spaced in the water flow direction from each other. The support structure is more flexible in the water flow direction than in the perpendicular direction to the water flow, so that small bending stresses are induced in the support structure and the axial stresses induced in the support structure by the weight and the buoyancy acting on the turbine and the bending stresses induced in the support structure by axial deformation of the turbine are kept below an allowable stress of material constituting the support structure.

Abstract: The outlet 38 of a turbine housing 18 may be sealed to a port 46 while at the same time mounting a turbine 10 and associated transmission 36 for vibration and shock isolation by locating elastomeric seal and turbine mounts 50, 52 on opposed walls 28 and 30 of the turbine housing 18 defining the outlet 38.

Abstract: Apparatus for sealing a joint between two components of a fluid turbine comprises a member having a surface contour conforming to at least a portion of a first mateable surface of one component, a biasing element for urging the member against the first mateable surface and a relieved feature terminating in a second mateable surface of the other component so that portions of the first and second mateable surfaces may sealingly engage. The apparatus may be disposed in the radially inward portion of a turbine shell and the area around the member may be relieved to accommodate unequal circumferential expansion between the radially inner and outer portion of the shell while maintaining sealing engagement between the first and second mateable surfaces.

Abstract: The stirrer vessel and stirrer shaft of a stirring apparatus are heated and carry an enamel coating on the surfaces coming into contact with the product. In order to prevent destruction of this enamel coating when the stirrer shaft is severely stressed, elastic intermediate members are arranged between a rigid support shaft and a shaft casing. The stuffing box is also held on the stirrer vessel by a further elastic intermediate member. An elastic packing between the fixed part of the stirrer vessel and the vessel cover fixed to the drive casing balances forces which are transferred from the vessel wall to the drive casing.

Abstract: Two rotationally symmetrically correlated components of a turbomachine, such as a gas turbine engine, define between them an air duct surrounding the axis of the components. A resilient band-like wall section extending radially from the first component bears resiliently in an axial direction against a wall section projecting radially from the second component to provide a seal for the duct. Another wall section of each component cooperate to form a radially extending tongue-in-groove joint, which may incorporate another seal for the duct, this joint permitting relative axial and radial movements between the two components. Means may be provided to maintain the fluid pressure within the duct higher than the pressure exterior thereto. The two components may be joined together by a bayonet-type connection. One of the components may comprise two members so that the member carrying part of the bayonet-type connection can be rotated with respect to the other member during assembly of the two components.

Abstract: In an exhaust-gas turbocharger having an uncooled gas duct, the hot gas casing is connected to the relatively cooler supporting casing by a supporting member resilient in the radial direction. The supporting member consists of an outer flange and an inner flange and of a diaphragm disposed therebetween and comprising at least one fold and two flanks extending predominantly in the axial direction. The coefficient of thermal expansion of the material of the diaphragm flanks is preferably from 5% to 40% higher than that of the hot gas casing.

Abstract: A liquid metal pump bearing support comprises a series of tangentially oriented spokes that connect the bearing cylinder to the pump internals structure. The spokes may be arranged in a plurality of planes extending from the bearing cylinder to the pump internals with the spokes in one plane being arranged alternately with those in the next plane. The bearing support structure provides the pump with sufficient lateral support for the bearing structure together with the capability of accommodating differential thermal expansion without adversely affecting pump performance.

Abstract: An annular ring 22 for an axial flow gas turbine engine disposed inwardly of an array of stator vanes 14 and between an annular flow path 18 for hot working medium gases and an annular flow path 20 for cooling air is disclosed. The ring abuttingly engages the array of stator vanes in the radial direction to provide radial support and abuttingly engages the array of stator vanes and an outer air seal block the intermixing of gases from the working medium flow path and gases from the cooling air flow path. The annular ring includes a first annular section 28 and a second annular section 30. The first annular section has an axial width to radial height ratio greater than one and the second annular section has an axial width to radial height ratio less than one to adapt the ring for axial flexibility and radial stiffness and to enable the ring to accommodate growth and axial growth between the outer air seal and the array of stator vanes while remaining within the elastic limit.

Abstract: Seal for two concentric tubular elements of a gas turbine, consisting of rings associated with each element and having facing grooves, and of a connector extending between the grooves and consisting of two annuli which are in concentric spaced relationship and are joined by a web.

Abstract: A seal means for confining cooling air to a cooling air flowpath extending between a case structure and a flowpath for hot working medium gases in a gas turbine engine is disclosed. Various construction details which enable the seal means to block the leakage of cooling air into the working medium flowpath are discussed. The seal means has a center section which expands axially in response to the temperature of the working medium gases to develop a sealing force.

Abstract: A seal member for a gas turbine engine is disclosed. Various construction details which ensure an adequate fatigue life and increase the sealing effectiveness of the member during engine operation are developed. A metal diaphragm extends from a nonrotating structure inwardly of the engine flow path to engage the stator vanes at engine operating temperature.

Abstract: A seal member for a gas turbine engine is disclosed. Various construction details which increase sealing effectiveness and which enable the damping of vibrations in a plurality of vanes are developed. The seal member is disposed between the engine case and a plurality of stator vanes. The seal member has a flexible center section which is compressed in the installed position.

Abstract: A gas turbine engine comprising an annular casing and a bearing housing located concentrically with the casing and in spaced relation thereto. An annular exhaust gas duct is formed between the bearing housing and the outer annular casing. The bearing housing includes a pair of concentric spaced-apart rings connected in a cantilevered manner. The outer ring is supported to the outer casing by angularly, spaced-apart, radially extending support members, and the inner ring includes a cylindrical inner surface to which a concentric bearing support member is tightly fitted therein. The concentric bearing support member includes angularly, spaced-apart, support contact means tightly engaging the inner cylindrical surface of the inner ring while the remainder of the bearing support is out of radial contact with the inner ring of the housing to allow for minimum thermal conduction, yet stressed for relief in the tightly fitting support member within the bearing support housing.

Abstract: A compensator for differential thermal expansion in a multi-stage barrel type centrifugal pump has a truncated conical body section and a plurality of leaf springs extending radially from said body section, the compensator is disposed in the multi-stage barrel type centrifugal pump between the outer casing and the end most interstage pumping assembly of a plurality of serially disposed interstage pumping assemblies in the centrifugal pump so that it is biased by the leaf springs to exert a controlled force in the direction of the end most interstage pumping assembly to permit movement between the serially disposed interstage pumping assemblies with variations in temperature arising during the operation of the centrifugal pump while continuing to maintain a tight seal between these respective interstage pumping assemblies.

Abstract: A low pressure turbine apparatus having a single casing member surrounding a rotatable member. The casing comprises six pieces which, when joined, provide an integrated single casing member. Suitable flex plates are provided to accommodate differential thermal expansion of the casing yet avoid thermal distortion of the apparatus. The stationary blading and inlet and extraction flow spaces are incorporated in a center section. Exhaust hood end sections with integral bearing housings are bolted to the center section through vertical joints. Axial brace pipes integral with the center section tie the end sections together and prevent movement of the bearings due to expansion of the higher temperatures in the inlet and extraction zones. Axial alignment of the stationary blading is provided at the center plane of the turbine by the use of integrally fabricated flex plates. The center section is insulated and exposed to atmospheric conditions.

Abstract: An outer ceramic shroud for a gas turbine engine includes a plurality of ceramic ring members each housing a rotating blade row of the turbine and further including ceramic stator vane stages located alternately between each of the ring members and having a radially outer rim portion thereon axially aligned with the ring members. The ring members and rims have tongue and groove means thereon for interconnection thereof into a continuous outer high temperature ceramic shroud maintained in axially assembled relationship by a pressure loaded piston member for applying a load to the shroud components during engine operation as a direct function of the discharge pressure of the engine compressor and a supplemental spring to load the shroud components when the discharge pressure drops, thereby to maintain the operative position of stator vane stages.