Patent US3887298A successfully refreshed from Google Patents.
US3887298A
Expired / Lapsed
US
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Apparatus for sealing turbine blade damper cavities
Assignee: RTX Corp
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Filing: 1974-05-30
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Granted: 1975-06-03
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Expires: 1994-05-30
Abstract
Abstract Apparatus to prevent leakage of working medium through the turbine blade damper cavities of a gas turbine engine is disclosed. A radial seal plate, having an inclined surface which projects into a damper cavity, extends between the neck extensions of two adjacent blades in the region between the turbine disk and the platforms of the blades; the seal plate closes off one end of the damper cavity. Inside the cavity is a vibration damper having two axially extending ridges separated circumferentially by a distance exceeding the gap between the platforms defining the cavity. The damper has a sloped surface adjacent to the inclined surface on the seal plate. During rotation of the engine centrifugal force causes the inclined surface of the seal plate to slide along the sloped surface of the damper until the seal plate is firmly seated against the disk and the neck extensions of the two adjacent blades. Simultaneously, the gap between the blade platforms is sealed by the damper which is held in place against the undersurfaces of the blade platforms.
Inventors
- 👤 John R Hess
- 👤 Joseph R Kozlin
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-05 12:55
CPC Classifications
F; F01; F01D; F01D5/00; F01D5/12; F01D5/22; F01D11/00; F01D11/005; F01D11/006; F01D5/30; F01D5/3007; F01D5/3015; Y; Y10; Y10S; Y10S416/00; Y10S416/50
Claims Analysis
Total Claims: 10
Claim 1
Independent Claim
240 words
In a gas turbine having an axis of rotation, a wheel assembly comprising: a turbine disk having a circumferentially extending rim with root connecting means spaced along the rim and first and second faces which are substantially perpendicular to the axis of rotation; a plurality of turbine blades extending radially from the disk, each blade having a root which engages the root connecting means and a platform spaced apart radially from the root by a neck extension; a plurality of seal plates, each of which abuts the first face of the disk at the rim and the neck extensions of two adjacent turbine blades and has a support section extending between the neck extensions of the adjacent blades; a plurality of vibration dampers each of which is located between the neck extensions of two adjacent blades in a position radially outward from the support of the seal plate, and has a sloped surface facing, and in contact with, the support section of the seal plate which is urged against the first face of the disk by axial components of centrifugal loads during rotation of the wheel assembly; a first sideplate which is in surface contact with the first face of the disk and covers the root portions of a plurality of turbine blades; and a second sideplate which is in surface contact with the second face of the disk and covers the root portions of a plurality of turbine blades.
Claim 2
Dependent Claim
240 words
In a gas turbine having an axis of rotation, a wheel assembly comprising: a turbine disk having a circumferentially extending rim with root connecting means spaced along the rim and first and second faces which are substantially perpendicular to the axis of rotation; a plurality of turbine blades extending radially from the disk, each blade having a root which engages the root connecting means and a platform spaced apart radially from the root by a neck extension; a plurality of seal plates, each of which abuts the first face of the disk at the rim and the neck extensions of two adjacent turbine blades and has a support section extending between the neck extensions of the adjacent blades; a plurality of vibration dampers each of which is located between the neck extensions of two adjacent blades in a position radially outward from the support of the seal plate, and has a sloped surface facing, and in contact with, the support section of the seal plate which is urged against the first face of the disk by axial components of centrifugal loads during rotation of the wheel assembly; a first sideplate which is in surface contact with the first face of the disk and covers the root portions of a plurality of turbine blades; and a second sideplate which is in surface contact with the second face of the disk and covers the root portions of a plurality of turbine blades.
Claim 3
Dependent Claim
240 words
In a gas turbine having an axis of rotation, a wheel assembly comprising: a turbine disk having a circumferentially extending rim with root connecting means spaced along the rim and first and second faces which are substantially perpendicular to the axis of rotation; a plurality of turbine blades extending radially from the disk, each blade having a root which engages the root connecting means and a platform spaced apart radially from the root by a neck extension; a plurality of seal plates, each of which abuts the first face of the disk at the rim and the neck extensions of two adjacent turbine blades and has a support section extending between the neck extensions of the adjacent blades; a plurality of vibration dampers each of which is located between the neck extensions of two adjacent blades in a position radially outward from the support of the seal plate, and has a sloped surface facing, and in contact with, the support section of the seal plate which is urged against the first face of the disk by axial components of centrifugal loads during rotation of the wheel assembly; a first sideplate which is in surface contact with the first face of the disk and covers the root portions of a plurality of turbine blades; and a second sideplate which is in surface contact with the second face of the disk and covers the root portions of a plurality of turbine blades.
Claim 4
Dependent Claim
240 words
In a gas turbine having an axis of rotation, a wheel assembly comprising: a turbine disk having a circumferentially extending rim with root connecting means spaced along the rim and first and second faces which are substantially perpendicular to the axis of rotation; a plurality of turbine blades extending radially from the disk, each blade having a root which engages the root connecting means and a platform spaced apart radially from the root by a neck extension; a plurality of seal plates, each of which abuts the first face of the disk at the rim and the neck extensions of two adjacent turbine blades and has a support section extending between the neck extensions of the adjacent blades; a plurality of vibration dampers each of which is located between the neck extensions of two adjacent blades in a position radially outward from the support of the seal plate, and has a sloped surface facing, and in contact with, the support section of the seal plate which is urged against the first face of the disk by axial components of centrifugal loads during rotation of the wheel assembly; a first sideplate which is in surface contact with the first face of the disk and covers the root portions of a plurality of turbine blades; and a second sideplate which is in surface contact with the second face of the disk and covers the root portions of a plurality of turbine blades.
Claim 5
Dependent Claim
28 words
The invention according to claim 1 wherein the support section has an inclined surface substantially parallel to, and in contact with, the sloped surface of the vibration damper.
Claim 6
Dependent Claim
112 words
The invention according to claim 1 wherein the vibration damper further has an end plate extension which abuts the second face of the disk at the rim and the neck extensions of the two adjacent blades, and a pair of sealing surfaces, each of which is in contact with the undersurface of the platform of one of the adjacent blades, whereby the end plate extension of the vibration damper is urged against the second face of the disk by axial components of centrifugal loads during rotation of the wheel assembly and whereby the sealing surfaces of the vibration damper are held in contact with the platforms by radial components of centrifugal loads.
Claim 7
Dependent Claim
34 words
The invention according to claim 1 wherein the first sideplate has a circumferential offset at its periphery which engages and retains the seal plates between the offset and the first face of the disk.
Claim 8
Dependent Claim
34 words
The invention according To claim 1 wherein the second sideplate has a circumferential offset at its periphery which engages and retains the vibration dampers between the offset and the second face of the disk.
Claim 9
Dependent Claim
152 words
In a gas turbine engine having an axis of rotation, a wheel assembly of the type wherein a plurality of blades is attached to a turbine disk and extend radially from the disk, the disk having a face which is substantially perpendicular to the axis of rotation and a circumferentially extending rim with root connecting means spaced about the rim, and each blade having a root which engages the root connecting means of the disk and a blade platform joined to the root by a neck extension, and wherein a plurality of seal plates is held in contact with the disk face and the neck extensions of two adjacent blades to prevent the leakage of working medium in the axial direction across the wheel assembly, the improvement which comprises: means responsive to centrifugal force to urge each seal plate against the face of the disk and to damp vibration in the blades.
Claim 10
Dependent Claim
152 words
In a gas turbine engine having an axis of rotation, a wheel assembly of the type wherein a plurality of blades is attached to a turbine disk and extend radially from the disk, the disk having a face which is substantially perpendicular to the axis of rotation and a circumferentially extending rim with root connecting means spaced about the rim, and each blade having a root which engages the root connecting means of the disk and a blade platform joined to the root by a neck extension, and wherein a plurality of seal plates is held in contact with the disk face and the neck extensions of two adjacent blades to prevent the leakage of working medium in the axial direction across the wheel assembly, the improvement which comprises: means responsive to centrifugal force to urge each seal plate against the face of the disk and to damp vibration in the blades.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1978-06-02 | 1978-12-02 | 1979-06-03 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1982-06-02 | 1982-12-02 | 1983-06-03 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1986-06-02 | 1986-12-02 | 1987-06-03 | $7700.00 | Window Closed / Lapsed |