Patent US3620641A successfully refreshed from Google Patents.
US3620641A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Bearing assembly
Assignee: Rolls Royce PLC
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Filing: 1969-10-13
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Granted: 1971-11-16
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Expires: 1989-10-13
Abstract
Abstract A gas turbine engine comprises in flow sequence compressor means, combustion means and turbine means, the compressor means and the turbine means comprising bladed rotors, a shaft supporting at least one of said bladed rotors, a bearing in which said shaft is mounted, a fixed substantially cylindrical engine casing, two axially spaced apart substantially radially extending annular panel members, said bearing being supported from the fixed casing by way of said panel members, at least one of said panel members having a plurality of angularly spaced-apart dished portions, said portions being secured to the other of said panel members to brace together and interconnect the panel members.
Inventors
- 👤 John Michael Storer Keen
- 👤 Maurice John Byett
- 👤 Francis Anthony Weston
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-05 15:42
CPC Classifications
F; F02; F02C; F02C7/00; F02C7/20; F01; F01D; F01D25/00; F01D25/16; F01D25/162; F16; F16C; F16C35/00; F16C2360/00; F16C2360/23
Claims Analysis
Total Claims: 27
Claim 1
Independent Claim
122 words
A gas turbine engine comprising in flow sequence compressor means, combustion means and turbine means, the compressor means and the turbine means comprising bladed rotors, a shaft supporting at least one of said bladed rotors, a bearing in which said shaft is mounted, a fixed substantially cylindrical engine casing, two axially spaced-apart substantially radially extending annular panel members, said bearing being supported from the fixed casing by way of said panel members, at least one of said panel members having a plurality of angularly spaced apart dished portions, said at least one panel member having corrugated portions between said dished portions, and said dished portions being secured to the other of said panel members to brace together and interconnect the panel members.
Claim 2
Dependent Claim
122 words
A gas turbine engine comprising in flow sequence compressor means, combustion means and turbine means, the compressor means and the turbine means comprising bladed rotors, a shaft supporting at least one of said bladed rotors, a bearing in which said shaft is mounted, a fixed substantially cylindrical engine casing, two axially spaced-apart substantially radially extending annular panel members, said bearing being supported from the fixed casing by way of said panel members, at least one of said panel members having a plurality of angularly spaced apart dished portions, said at least one panel member having corrugated portions between said dished portions, and said dished portions being secured to the other of said panel members to brace together and interconnect the panel members.
Claim 3
Dependent Claim
20 words
A gas turbine engine as claimed in claim 1 wherein the dished portions are substantially lozenge shaped, as herein defined.
Claim 4
Dependent Claim
27 words
A gas turbine engine as claimed in claim 2 wherein the dished portions each have major and minor axes, the major axes extending radially of the shaft.
Claim 5
Dependent Claim
15 words
A gas turbine engine as claimed in claim 2 wherein the dished portions are elliptical.
Claim 6
Dependent Claim
32 words
A gas turbine engine as claimed in claim 1 wherein the corrugated portions are constituted by elongated dished portions, the major axis of each elongated dished portion extending radially of the shaft.
Claim 7
Dependent Claim
50 words
A gas turbine engine as claimed in claim 1 wherein said dished portions are of relatively rounded shape, further dished portions being interposed between the relatively rounded dished portions, and being of relatively elongated shape, each relatively elongated dished portion having a major axis which extends radially of the shaft.
Claim 8
Dependent Claim
31 words
A gas turbine engine as claimed in claim 1 comprising in each dished portion a deeper dished portion which secures the said dished portion to the other of said panel members.
Claim 9
Dependent Claim
43 words
A gas turbine engine as claimed in claim 1 comprising means defining apertures in regions of at least one panel member which are not dished, the edges of the apertures being deformed out of the planes of the apertures, forming stiffened rims therefor.
Claim 10
Dependent Claim
24 words
A gas turbine engine as claimed in claim 1 wherein the dished portions are secured to the other of said panel members by welding.
Claim 11
Dependent Claim
24 words
A gas turbine engine as claimed in claim 1 wherein the said dished portions are integrally formed in said at least one panel member.
Claim 12
Dependent Claim
40 words
A gas turbine engine as claimed in claim 1 wherein said angularly spaced-apart dished portions are provided in both panels, said portions being arranged in pairs, one from each panel, the portions of each pair having their bases secured together.
Claim 13
Dependent Claim
59 words
A gas turbine engine as claimed in claim 11, comprising for each said pair of dished portions a connecting member extending between said bases securing them together, said connecting member being an open-ended tubular member having an internal dividing wall, each open end being respectively secured in an aperture in the respective base, forming a deeper dished portion therein.
Claim 14
Dependent Claim
41 words
A gas turbine engine as claimed in claim 1 including an axially extending bearing support ring, said bearing being supported by said ring and said panel members being connected to said ring, a further bearing also being supported by the ring.
Claim 15
Dependent Claim
47 words
A gas turbine engine as claimed in claim 1 including a plurality of angularly spaced-apart struts secured to said engine casing, said panel members being secured to said struts, a plurality of hollow nozzle guide vanes, each of said struts extending through one of said guide vanes.
Claim 16
Dependent Claim
120 words
A gas turbine engine comprising in flow sequence compressor means, combustion means, and turbine means, a shaft supporting at least one of said compressor means and said turbine means, a bearing in which said shaft is mounted, a fixed cylindrical engine casing, two axially spaced substantially radially extending annular panel members, said bearing being supported from the fixed casing by way of said panel members, at least one of said panel members having a plurality of angularly spaced-apart dished portions each of which is secured to the other of said panel members to brace together and interconnect the same, said dished portions being elliptical in shape, said at least one panel member having corrugated portions between the dished portions thereof.
Claim 17
Dependent Claim
120 words
A gas turbine engine comprising in flow sequence compressor means, combustion means, and turbine means, a shaft supporting at least one of said compressor means and said turbine means, a bearing in which said shaft is mounted, a fixed cylindrical engine casing, two axially spaced substantially radially extending annular panel members, said bearing being supported from the fixed casing by way of said panel members, at least one of said panel members having a plurality of angularly spaced-apart dished portions each of which is secured to the other of said panel members to brace together and interconnect the same, said dished portions being elliptical in shape, said at least one panel member having corrugated portions between the dished portions thereof.
Claim 18
Dependent Claim
24 words
A gas turbine engine as claimed in claim 15 wherein the said dished portions are integrally formed in said at least one panel member.
Claim 19
Dependent Claim
40 words
A gas turbine engine as claimed in claim 15 wherein said angularly spaced-apart dished portions are provided in both panels, said portions being arranged in pairs, one from each panel, the portions of each pair having their bases secured together.
Claim 20
Dependent Claim
41 words
A gas turbine engine as claimed in claim 15 including an axially extending bearing support ring, said bearings being supported by said ring and said panel members being connected to said ring, a further bearing also being supported by the ring.
Claim 21
Dependent Claim
47 words
A gas turbine engine as claimed in claim 15 including a plurality of angularly spaced-apart struts secured to said engine casing, said panel members being secured to said struts, a plurality of hollow nozzle guide vanes, each of said struts extending through one of said guide vanes.
Claim 22
Dependent Claim
148 words
A gas turbine engine comprising in flow sequence compressor means, combustion means and turbine means, the compressor means and the turbine means comprising bladed rotors, a shaft supporting at least one of said bladed rotors, a bearing in which said shaft is mounted, a fixed substantially cylindrical engine casing, two axially spaced-apart substantially radially extending annular panel members, said bearing being supported from the fixed casing by way of said panel members, at least one of said panel members having a plurality of angularly spaced-apart dished portions, said dished portions being secured to the other of said panel members to brace together and interconnect the panel members, said dished portions being of relatively rounded shape, and further dished portions being interposed between the relatively rounded dished portions and being of relatively elongated shape, each relatively elongated dished portion having a major axis which extends radially of the shaft.
Claim 23
Dependent Claim
148 words
A gas turbine engine comprising in flow sequence compressor means, combustion means and turbine means, the compressor means and the turbine means comprising bladed rotors, a shaft supporting at least one of said bladed rotors, a bearing in which said shaft is mounted, a fixed substantially cylindrical engine casing, two axially spaced-apart substantially radially extending annular panel members, said bearing being supported from the fixed casing by way of said panel members, at least one of said panel members having a plurality of angularly spaced-apart dished portions, said dished portions being secured to the other of said panel members to brace together and interconnect the panel members, said dished portions being of relatively rounded shape, and further dished portions being interposed between the relatively rounded dished portions and being of relatively elongated shape, each relatively elongated dished portion having a major axis which extends radially of the shaft.
Claim 24
Dependent Claim
31 words
A gas turbine engine as claimed in claim 20 comprising in each dished portion a deeper dished portion which secures the said dished portion to the other of said panel members.
Claim 25
Dependent Claim
45 words
A gas turbine engine as claimed in claim 20 comprising means defining apertures in regions of the said at least one panel member which are not dished, the edges of the apertures being deformed out of the planes of the apertures, forming stiffened rims therefor.
Claim 26
Dependent Claim
151 words
A gas turbine engine comprising in flow sequence compressor means, combustion means and turbine means, the compressor means and the turbine means comprising bladed rotors, a shaft supporting at least one of said bladed rotors, a bearing in which said shaft is mounted, a fixed substantially cylindrical engine casing, two axially spaced-apart substantially radially extending annular panel members, said bearing being supported from the fixed casing by way of said panel members, both panel members having a plurality of angularly spaced-apart dished portions, said dished portions being arranged in pairs, one from each panel member, and a connecting member for each said pair of dished portions extending between the bases of said dished portions and securing them together, each said connecting member being an open-ended tubular member having an internal dividing wall, each open end being respectively secured in an aperture in the respective base, forming a deeper dished portion therein.
Claim 27
Dependent Claim
151 words
A gas turbine engine comprising in flow sequence compressor means, combustion means and turbine means, the compressor means and the turbine means comprising bladed rotors, a shaft supporting at least one of said bladed rotors, a bearing in which said shaft is mounted, a fixed substantially cylindrical engine casing, two axially spaced-apart substantially radially extending annular panel members, said bearing being supported from the fixed casing by way of said panel members, both panel members having a plurality of angularly spaced-apart dished portions, said dished portions being arranged in pairs, one from each panel member, and a connecting member for each said pair of dished portions extending between the bases of said dished portions and securing them together, each said connecting member being an open-ended tubular member having an internal dividing wall, each open end being respectively secured in an aperture in the respective base, forming a deeper dished portion therein.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1974-11-15 | 1975-05-17 | 1975-11-16 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1978-11-15 | 1979-05-17 | 1979-11-16 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1982-11-15 | 1983-05-17 | 1983-11-16 | $7700.00 | Window Closed / Lapsed |