초록 ▼

A gas turbine having rotor discs (9), a disc cavity (13) and a stator stage (25) extending to the disc cavity (13). Seal housing flanges (43, 44) extend from a seal housing (29) of the stator stage (25). Rotor flanges (41i, 41o) extend from a rotor disk (9-1). An inner rotor flange (41i) and first s

A gas turbine having rotor discs (9), a disc cavity (13) and a stator stage (25) extending to the disc cavity (13). Seal housing flanges (43, 44) extend from a seal housing (29) of the stator stage (25). Rotor flanges (41i, 41o) extend from a rotor disk (9-1). An inner rotor flange (41i) and first seal housing flange (43) are inward from a second seal housing flange (44). One rotor flange (41o) is outward from the second seal housing flange (44). The inner rotor flange (41i) and first seal housing flange (43) extend toward one another to limit movement of main gas flow (17). An inlet (47) injects air (50) between the outward rotor flange (41o) and second seal housing flange (44).

대표청구항 ▼

1. A gas turbine comprising: a turbine casing;a rotor mounted for rotation within the turbine casing and comprising a rotor shaft and at least a first stage upstream rotor disc and a second stage downstream rotor disc axially displaced on the rotor shaft to form an interstage disc cavity therebetwee

1. A gas turbine comprising: a turbine casing;a rotor mounted for rotation within the turbine casing and comprising a rotor shaft and at least a first stage upstream rotor disc and a second stage downstream rotor disc axially displaced on the rotor shaft to form an interstage disc cavity therebetween, the rotor having a plurality of rotor blades extending radially outward from the rotor discs into a main gas flow, the second stage rotor disc positioned in a downstream direction with respect main gas flow from the first stage upstream rotor disk;a stator comprising a plurality of stator stages, a first of the stator stages extending radially inward to the interstage disc cavity from the turbine casing toward the rotor shaft, the plurality of stator stages providing multiple stator vanes axially aligned with the rotor blades in the main gas flow and terminating radially inwardly with a seal housing which provides a seal about the rotor shaft,the first of the stator stages including an attachment portion connecting the seal housing to at least one stator vane, wherein a combination, comprising the seal housing, and the first stage rotor disc, including a surface of the first stage rotor disc which faces the seal housing, and the second stage rotor disc, including a surface of the second stage rotor disc facing the seal housing, form a seal assembly about the interstage disc cavity, the seal housing including a first portion facing the surface of the first stage rotor disc and a second portion facing the first surface of the second stage rotor disc;first and second seal housing flanges each extending outward from the first portion of the seal housing, each extending toward the surface of the first stage rotor disc;inner and outer rotor flanges each extending outward from the first stage upstream rotor disk along the surface of the first stage rotor disc toward the first of the stator stages, wherein:the inner rotor flange and first seal housing flange are positioned radially inward relative to the second seal housing flange and the outer rotor flange is positioned radially outward relative to the second seal housing flange,the outer rotor flange functions as a rim seal,the inner rotor flange and the first seal housing flange extend toward one another in close proximity to limit ingress of main gas flow along the rotor shaft,wherein a portion of the interstage disc cavity between the seal housing and the surface of the first stage rotor disc which faces the seal housing includes at least first and second interconnected flow regions where (i) the first flow region is positioned radially outward with respect to the second flow region so that the first flow region must initially receive a portion of the main gas flow before that portion is received by the second flow region and (ii) the first flow region is between the outer rotor flange and the second seal housing flange and (iii) the second flow region is between the inner rotor flange and the first seal housing flange, andthe first portion of the seal housing includes a cooling air inlet positioned to inject air directly into the first flow region of the disc cavity between the outer rotor flange and the second seal housing flange such that air injected directly into the first flow region must flow through the first flow region before flowing into the second flow region. 2. The gas turbine of claim 1 wherein the second seal flange protrudes toward the first surface of the first stage rotor disc so that in the outer region of the disc cavity, when a portion of the main gas flow enters the outer region of the disc cavity, a circular flow occurs in the outer region as air is injected from the cooling air inlet into the outer region. 3. The gas turbine of claim 1 wherein the inner and outer rotor flanges each extend outward along the surface of the first stage rotor disc toward the first portion of the seal housing or toward the attachment portion which connects the seal housing to the stator vane in the first of the stator stages. 4. The gas turbine of claim 1 further including a labyrinth seal positioned to provide a seal between the seal housing and the rotor shaft, the disc cavity including a first inner region bounded by the combination of the inner rotor flange, the first seal flange and the second seal flange, and a second inner region bounded by the first seal housing flange and the labyrinth seal. 5. The gas turbine of claim 4 wherein, when a portion of the main gas flow enters the outer region of the disc cavity, a circular flow occurs in the first inner region. 6. The gas turbine of claim 1 wherein the rotor includes additional rotor discs spaced axially along the rotor shaft to form additional interstage disc cavities, and the stator includes additional stator stages each extending radially inward into an additional interstage disc cavity and having a seal assembly sealing against the rotor shaft. 7. A method for cooling components in a gas turbine of the type having a rotor and a stator, the rotor, mounted for rotation within a turbine casing based on movement of a main gas flow, including a rotor shaft and at least a first stage upstream rotor disc and a second stage downstream rotor discs axially displaced on the rotor shaft to form an interstage disc cavity, the rotor having a plurality of rotor blades extending radially outward from the rotor discs,the stator including a first stage extending radially inward to the interstage disc cavity and terminating radially inwardly with a seal housing which provides a seal about the rotor shaft, first and second seal housing flanges each extending outward from the seal housing and toward the first stage rotor disc, the first stage rotor disc including inner and outer rotor flanges each extending outward therefrom toward the seal housing of the first stage of the stator, the outer rotor flange positioned to function as a rim seal, the method comprising:forming at least first and second interconnected flow regions in the disc cavity by positioning the inner rotor flange and first seal housing flange radially inward relative to the second seal housing flange and positioning the outer rotor flange radially outward relative to the second seal housing flange,with (i) the first flow region is-positioned radially outward with respect to the second flow region so that the first flow region must initially receives a portion of the main gas flow before that portion is received by the second flow region, and (ii) the first flow region is between the outer rotor flange and the second seal housing flange and (iii) the second flow region is between the inner rotor flange and the first seal housing flange; andinjecting a flow of air, different from the main gas flow, directly into the first flow region so that the air injected directly into the first flow region must flow through the first flow region before flowing into the second flow region and the portion of the main gas flow which is received by the second flow region is mixed with the flow of air before reaching the second flow region. 8. The method of claim 7 wherein the seal housing is positioned in the disc cavity, having a seal housing surface spaced away from a surface of the first stage rotor disc, wherein: the inner rotor flange and first seal housing flange extend toward one another in close proximity to limit movement of main gas flow along the rotor shaft, so that the first flow region is between the outer rotor flange and the second seal housing flange and the second flow region extends between the first and second seal flanges. 9. The method of claim 8 wherein the step of injecting the flow of air is effected by forming a cooling air inlet through the seal housing so that the air is injected in a portion of the first flow region positioned between the outer rotor flange and the second seal housing flange.