Patent US4311433A successfully refreshed from Google Patents.
US4311433A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Transpiration cooled ceramic blade for a gas turbine
Assignee: Siemens Energy Inc
•
Filing: 1979-01-16
•
Granted: 1982-01-19
•
Expires: 1999-01-16
Abstract
Abstract A transpiration cooled ceramic blade for a gas turbine is shown wherein a spar or strut member defining a root portion and an airfoil portion provides the main structural component of the blade. The air foil portion contains longitudinal grooves in the surface in flow communication with an air flow passage in the root portion and a flexible perforated ceramic tape is wrapped around the air foil portion with the perforations therein in registry with the grooves in the core. The flexible ceramic tape and the strut assembly are heated initially to a low temperature to drive off the binder forming the tape and then heated to a relatively high temperature to fuse the ceramic component of the tape together and to the strut to form a unitary blade structure with internal air flow paths and transpiratin cooling orifices through the skin.
Inventors
- 👤 Raymond J. Bratton
- 👤 Clarence A. Andersson
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-31 15:19
CPC Classifications
F; F01; F01D; F01D5/00; F01D5/12; F01D5/14; F01D5/18; F01D5/182; F01D5/184; F01D5/28; F01D5/284; Y; Y10; Y10T; Y10T29/00; Y10T29/49; Y10T29/49316; Y10T29/49336; Y10T29/49339; Y10T29/49341
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
155 words
A transpiration cooled blade for a combustion turbine engine, said blade comprising a central strut member defining an airfoil portion and a root portion, a plurality of grooves formed in the air foil portion and in flow communication with an air delivery channel in the root portion, a ceramic skin enveloping the air foil portion of the strut and bonded thereto, said skin comprising an innermost layer defining a plurality of apertures therethrough in flow communication with said grooves, an outermost layer defining a plurality of apertures therethrough sufficiently greater in number than said apertures in said innermost layer to provide distributed air flow through the exterior of said blade, layer means positioned between said innermost layer and said outermost layer defining a plurality of flow passages therethrough in flow communication with said apertures of said innermost and said outermost layers permitting cooling air to flow from said grooves to the exterior of said blade.
Claim 2
Dependent Claim
155 words
A transpiration cooled blade for a combustion turbine engine, said blade comprising a central strut member defining an airfoil portion and a root portion, a plurality of grooves formed in the air foil portion and in flow communication with an air delivery channel in the root portion, a ceramic skin enveloping the air foil portion of the strut and bonded thereto, said skin comprising an innermost layer defining a plurality of apertures therethrough in flow communication with said grooves, an outermost layer defining a plurality of apertures therethrough sufficiently greater in number than said apertures in said innermost layer to provide distributed air flow through the exterior of said blade, layer means positioned between said innermost layer and said outermost layer defining a plurality of flow passages therethrough in flow communication with said apertures of said innermost and said outermost layers permitting cooling air to flow from said grooves to the exterior of said blade.
Claim 3
Dependent Claim
16 words
A structure according to claim 1 wherein said ceramic skin is formed of a ceramic tape.
Claim 4
Dependent Claim
15 words
A structure according to claim 1 wherein said airfoil portion of said structure is ceramic.
Claim 5
Dependent Claim
11 words
A structure according to claim 1 wherein said strut is ceramic.
Claim 6
Dependent Claim
37 words
A structure according to claim 1 wherein said blade includes separate platform segments, assembled in facing engagement with the root portion of said strut and cooperating therewith to define an enclosed air delivery channel to said grooves.
References Cited (Backward Citations)
GB653267A
Cited
US2751188A
Cited
US3011760A
Cited
US2873947A
Cited
US3293072A
Cited
US3950114A
Cited
US3620643A
Cited
US3672787A
Cited
US3656863A
Cited
US3709632A
Cited
US3886647A
Cited
US3810711A
Cited
US4022542A
Cited
US4067662A
Cited
US4004056A
Cited
US4118146A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1985-01-18 | 1985-07-20 | 1986-01-19 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1989-01-18 | 1989-07-20 | 1990-01-19 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1993-01-18 | 1993-07-20 | 1994-01-19 | $7700.00 | Window Closed / Lapsed |