US3597109A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Gas turbine engine axial flow multistage compressor
Assignee: Rolls Royce PLC
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Filing: 1969-05-22
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Granted: 1971-08-03
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Expires: 1989-05-22
Abstract
Abstract The invention concerns a gas turbine engine axial flow multistage compressor having a rotor member, and a plurality of platform elements each of which has rotor blade members mounted thereon and each of which is itself disposed radially outwardly of and spaced from the rotor member, the plurality of platform elements defining an annular platform member and the axially consecutive annular platform member of different stages of rotor blade members contacting each other to form a drumlike structure.
Inventors
- 👤 James Alexander Petrie
- 👤 Kenneth Edward George Bracey
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-07 06:48
CPC Classifications
F; F01; F01D; F01D5/00; F01D5/30; F01D5/02; F01D5/06
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
163 words
A gas turbine engine axial flow multistage compressor comprising: a plurality of axially spaced rotor discs; each of said rotor discs supporting a plurality of angularly spaced blade assemblies, the angularly spaced blade assemblies of one of said rotor discs being axially spaced with respect to the angularly spaced blade assemblies of an adjacent one of said discs; each blade assembly of said plurality of angularly spaced blade assemblies being an integral structure including a root portion mounted in a slot in a respective rotor disc, a connecting structure extending from the root portion radially outwardly of the respective rotor disc, a platform element disposed on the outer end of said connecting structure, and a plurality of rotor blade members mounted on said platform element; and said platform elements of said angularly spaced blade assemblies for the respective rotor discs defining an annular platform member and consecutive annular platform members of axially spaced-apart rotor discs contacting one another to form a drumlike structure.
Claim 2
Dependent Claim
163 words
A gas turbine engine axial flow multistage compressor comprising: a plurality of axially spaced rotor discs; each of said rotor discs supporting a plurality of angularly spaced blade assemblies, the angularly spaced blade assemblies of one of said rotor discs being axially spaced with respect to the angularly spaced blade assemblies of an adjacent one of said discs; each blade assembly of said plurality of angularly spaced blade assemblies being an integral structure including a root portion mounted in a slot in a respective rotor disc, a connecting structure extending from the root portion radially outwardly of the respective rotor disc, a platform element disposed on the outer end of said connecting structure, and a plurality of rotor blade members mounted on said platform element; and said platform elements of said angularly spaced blade assemblies for the respective rotor discs defining an annular platform member and consecutive annular platform members of axially spaced-apart rotor discs contacting one another to form a drumlike structure.
Claim 3
Dependent Claim
23 words
A compressor as claimed in claim 1 in which each platform element carries a plurality of rotor blade members of a same stage.
Claim 4
Dependent Claim
22 words
A compressor as claimed in claim 1 in which each platform element carries a plurality of rotor blade members of different stages.
Claim 5
Dependent Claim
33 words
A compressor as claimed in claim 1 in which said connecting structure of each blade assembly comprises at least one rib member angularly spaced from a rib member of an adjacent blade assembly.
Claim 6
Dependent Claim
34 words
A compressor as claimed iN claim 1 in which adjacent angularly spaced blade assemblies have root portions which contact each other and which are mounted in a common slot in the respective rotor disc.
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) | 1974-08-02 | 1975-02-01 | 1975-08-03 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1978-08-02 | 1979-02-01 | 1979-08-03 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1982-08-02 | 1983-02-01 | 1983-08-03 | $7700.00 | Window Closed / Lapsed |