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US 5,310,319 AGranted
Free standing turbine disk sideplate assembly
AssigneeUnited Technologies Corporation
InventorsParker A. Grant, Stephen D. Hoyt
Life of this patent
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AssigneeUnited Technologies Corporation
InventorsParker A. Grant, Stephen D. Hoyt
Estimating the term…
A gas turbine engine having a turbine rotor assembly with a free standing sideplate assembly is disclosed. Various construction details are developed which provide a sideplate assembly which is not radially or axially supported by the web or rim of the adjacent disk. In one particular embodiment, a rotor assembly includes a rotor disk, having a rim, a web, and a bore, and a sideplate assembly, having a web and a bore. The web of the sideplate is radially supported by the bore of the sideplate and includes a disk seal and an aperture. The disk seal is engaged with the rotor disk and has an axially directed seal force provided by an axially interfering fit between the sideplate and rotor disk. The aperture provides fluid communication between a source of cooling fluid and the rotor disk.
A gas turbine engine having a longitudinal axis and an axially disposed flow path defining a passage for working fluid, the gas turbine engine including a rotor assembly having a rotor disk and sideplate assembly, the rotor disk having a rotor self-sustaining radius and including a rotor disk bore disposed radially within the rotor self-sustaining radius and a rotor web disposed radially outward of the rotor self-sustaining radius, the sideplate assembly being positioned axially adjacent to the rotor disk and defining a disk cavity therebetween, the sideplate assembly including a sideplate disk having a sideplate self-sustaining radius, a sideplate bore disposed radially within the sideplate self-sustaining radius, and a sideplate web disposed radially outward of the sideplate self-sustaining radius, locating means disposed on the sideplate bore and engaged with the rotor disk bore, the sideplate blocking the passage of working fluid into the disk cavity such that engagement between working fluid and the rotor web is blocked, and wherein the sideplate assembly is not axially or radially supported by the disk web.
A rotor assembly for a gas turbine engine having a longitudinal axis and an axially disposed flow path defining a passage for working fluid, the rotor assembly including a rotor disk and a sideplate assembly, the rotor disk having a rotor self-sustaining radius and including a rotor disk bore disposed radially within the rotor self-sustaining radius and a rotor web disposed radially outward of the rotor self-sustaining radius, the sideplate assembly being free standing, positioned axially adjacent to the rotor disk and defining a disk cavity therebetween, the sideplate assembly including a sideplate disk having a sideplate self-sustaining radius, a sideplate bore disposed radially within the sideplate self-sustaining radius, and a sideplate web disposed radially outward of the sideplate self-sustaining radius, locating means disposed on the sideplate bore and engaged with the rotor disk bore, the sideplate blocking the passage of working fluid into the disk cavity such that engagement between working fluid and the rotor web is blocked, and wherein the sideplate assembly is not axially or radially supported by the disk web.
Dependencies are inferred from the claim text.