Patent US4307993A successfully refreshed from Google Patents.
US4307993A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Air-cooled cylinder with piston ring labyrinth
Assignee: Honeywell International Inc
•
Filing: 1980-02-25
•
Granted: 1981-12-29
•
Expires: 2000-02-25
Abstract
Abstract A turbine cylinder is in contact at its outer surface with split rings which are held in place in annular slots in a cylindrically extending ring holder. The rings, while remaining in contact with the outer surface of the cylinder, are allowed to expand and contract within their respective slots. Notches are constructed at the inner circumference of the rings to form a labyrinth type cooling passage in conjunction with the outer surface of the turbine cylinder.
Inventors
- 👤 Edward O. Hartel
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-04 18:13
CPC Classifications
F; F01; F01D; F01D11/00; F01D11/08; F01D11/14; F01D11/20; F01D11/24
Claims Analysis
Total Claims: 7
Claim 1
Independent Claim
129 words
In a gas turbine engine a turbine blade shroud assembly comprising: an inner shroud member mounted on the engine structure and extending into the turbine blade clearance area to surround the turbine blades; an outer shroud member fixed to the engine structure and surrounding the inner shroud member at a radial distance therefrom; said outer shroud member having a plurality of radially extending slots constructed at axially spaced intervals in its inner surface; and a plurality of split rings mounted for sliding radial motion in the annular slots; said rings extending radially inward to engage the inner shroud member; thereby forming annular passages between the axially spaced ring and the inner shroud member, said rings having circumferentially spaced notches on their inner surface to communicate between the annular passages.
Claim 2
Dependent Claim
129 words
In a gas turbine engine a turbine blade shroud assembly comprising: an inner shroud member mounted on the engine structure and extending into the turbine blade clearance area to surround the turbine blades; an outer shroud member fixed to the engine structure and surrounding the inner shroud member at a radial distance therefrom; said outer shroud member having a plurality of radially extending slots constructed at axially spaced intervals in its inner surface; and a plurality of split rings mounted for sliding radial motion in the annular slots; said rings extending radially inward to engage the inner shroud member; thereby forming annular passages between the axially spaced ring and the inner shroud member, said rings having circumferentially spaced notches on their inner surface to communicate between the annular passages.
Claim 3
Dependent Claim
36 words
In a gas turbine engine, a turbine blade shroud assembly as described in claim 1 further comprising a source of pressurized cooling air communicating with the annular passages between the axially spaced rings through the notches.
Claim 4
Dependent Claim
39 words
In a gas turbine engine, a turbine blade shroud assembly as described in claim 2 wherein the cooling air is exhausted forward around the edge of the inner shroud to film cool the inner surface of said inner shroud.
Claim 5
Dependent Claim
85 words
In a gas turbine engine, a turbine blade shroud assembly as described in claim 1 wherein the split rings are constructed identically and include an index tab extending radially outward from its circumference and the slots are constructed with a positioning hole to receive the index tab, said holes in each slot being spaced about the circumference of the slot relative to the adjacent slot in order to angularly offset the notches in the rings and form a labyrinth flow path for the cooling air.
Claim 6
Dependent Claim
41 words
In a gas turbine engine, a turbine blade shroud assembly as described in claim 1 further comprising a spring member mounted in the radially extending slots radially outward from the split rings to bias said rings in the radially inward direction.
Claim 7
Dependent Claim
45 words
In a gas turbine engine, a turbine blade shroud assembly as described in claim 1 wherein the inner and outer shroud members are mounted to separate portions of the engine structure in order to allow relative movement between said shroud members in the axial direction.
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) | 1984-12-28 | 1985-06-29 | 1985-12-29 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1988-12-28 | 1989-06-29 | 1989-12-29 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1992-12-28 | 1993-06-29 | 1993-12-29 | $7700.00 | Window Closed / Lapsed |