A compressor may include first and second scrolls and a seal. The first scroll includes a first end plate and a first spiral wrap extending from the first end plate. The first end plate may define a discharge passage and an annular recess surrounding the discharge passage. The second scroll includes a second end plate and a second spiral wrap extending from the second end plate. The first and second spiral wraps cooperate to define a plurality of fluid pockets. The seal may be at least partially received in the annular recess and may cooperate with the first scroll to define a biasing chamber receiving fluid at an intermediate pressure. The seal may include inner and outer diametrical surfaces. The inner diametrical surface may include a plurality of first annular grooves. The outer diametrical surface may include a plurality of second annular grooves.

A segmented seal and segmented seal assembly (10) are disclosed. An embodiment of a radial seal assembly includes a plurality of seal segments (12) that may interconnect to form a seal ring, each seal segment having a male joint end (20) and a female joint end (30). A male joint end of one seal segment may be configured to interconnect with a female joint end of an adjacent seal segment to provide a joint interface (50). In embodiments, the male joint end may include a shallow groove or pad (40) on an inner diameter of the male joint end, and the male joint end and the female joint end may be configured to provide a seal at the joint interface. With embodiments, the female joint end may include a deep groove or pad (60) on an inner diameter of the female joint end and/or may include a vent hole (70) that is isolated from the shallow groove.

A seal assembly for a bearing compartment of a gas turbine engine includes a seal carrier, a seal element, a seal plate, and a trough. At least a portion of the seal element is within the seal carrier. The seal plate is in contact with the seal element and is configured to rotate relative to the seal element. The trough extends around the seal plate and comprises an annular channel positioned to capture oil slung from the seal plate.

The turbomachine comprises a stationary casing with a rotating member configured to rotate about a rotation axis in the stationary casing. The turbomachine further includes a rotating balance drum, arranged for co-rotation with the rotating member. A stationary sleeve is arranged in a fixed relationship with the stationary casing and surrounds the balance drum. The stationary sleeve comprises a plurality of consecutively arranged sleeve sections. A fluid channel is defined by an outer surface of the balance drum and an inner surface of the stationary sleeve. Between at least one pair of sequentially arranged upstream sleeve section and downstream sleeve section an annular chamber is provided, fluidly coupled to the fluid channel. Shunt holes are arranged on the upstream sleeve section, each shunt hole having a shunt hole inlet on an inner surface of the upstream sleeve section, and a shunt hole outlet in the annular chamber.

The invention relates to a sealing segment for sealing between a stationary component and a rotating component. The sealing segment having a passage that extends so as to enable pressure balancing between radial ends of the sealing segment so by providing a seal that can ensure a minimum seal distance is maintained without the need for the complexities of actuators or other mechanical devices.

A sealing assembly includes a first machine component having a seal groove defined by radially oriented jacket support and energizer positioning walls and an energizer compressing wall that faces axially toward a second machine component. A seal located within the seal groove has an energizer element and a telescoping jacket. The jacket has a first leg portion having a jacket sealing surface facing toward the second machine component and an energizer contacting wall facing toward the energizer element. The energizer element is compressed between the energizer contacting and energizer compressing walls and loads the jacket sealing surface against the second machine component. A jacket second leg portion extends generally axially and has an energizer supporting wall facing toward the energizer element and a supported wall facing radially and adjoining the jacket support wall. The second leg portion is interposed between the energizer element and the jacket support wall.

A contra-flow strip for inhibiting leakage of a fluid between a rotating member and a stationary member includes, for example, a base supportable by the stationary member coaxially around the rotating member, and means, extending from the base coaxially towards the rotating member between a low pressure region and a high pressure region, for generating a contra flow of a portion of a tangential flow of fluid in the low pressure region to the high pressure region between the stationary member and the rotating member.

An intershaft seal assembly for use between an inner shaft and an outer shaft within a turbine engine is presented. The seal assembly includes a sealing ring, centrifugal retaining plates, and end rings. The sealing ring further includes a plurality of asymmetric ring segments whereby each asymmetric ring segment further includes a vertical flange and horizontal flanges extending from the vertical flange in a non-symmetric arrangement. At least one slot is disposed along each horizontal flange. The sealing ring is interposed between the centrifugal retaining plates. Each centrifugal retaining plate includes a plurality of tabs extending therefrom. Each tab is engaged by one slot. The sealing ring and the centrifugal retaining plates are interposed between the end rings. Each centrifugal retaining plate is directly interposed between one horizontal flange and one end ring. The vertical flange extends from between the end rings in the direction of the outer shaft. A non-contact seal is formed between an outer sealing surface along the vertical flange and an inner sealing surface along the outer shaft.

A sealing apparatus for sealing between a rotary shaft 11 and a housing 12 that can be rotated relative to each other, having a circular ring body 3 provided on the rotary shaft 11 and a seal lip body 6 made of a flexible material provided on the housing 12, wherein the seal lip body 6 has a discharge fin 8 on the outer peripheral side of a sealing part 6a which makes sliding contact with the circular ring body 3, and when the two members 11 and 12 rotate relative to each other, the surface of the discharge fin 8 on the side advancing relative to the circular ring body 3 composes an inclined surface receding more on the front edge side than the base end side of the discharge fin 8, and by this inclined surface, oil is discharged away from the sealing portion 6a.

An intershaft seal assembly for use between an inner shaft and an outer shaft rotatable within a turbine engine is presented. The seal assembly includes a sealing ring, an inner ring, and a pair of end rings. The sealing ring further includes a plurality of asymmetric ring segments whereby each asymmetric ring segment further includes a vertical flange and a pair of horizontal flanges extending from the vertical flange in a non-symmetric arrangement. The non-symmetric seal geometry provides an axial force balance thereby reducing wear and increasing seal life. The sealing ring is disposed about the inner ring. The inner ring includes a plurality of ridges that engage the asymmetric ring segments so as to prevent rotation of the asymmetric ring segments with respect to the inner shaft. The end rings are disposed about the sealing ring and the inner ring. The horizontal flanges separately contact the end rings so that the vertical flange extends from and between the end rings in the direction of the outer shaft. A non-contact seal is formed between an outer sealing surface along the vertical flange and an inner sealing surface along the outer shaft.