Rotary kinetic fluid motors or pumps – With passage in blade – vane – shaft or rotary distributor...
Reexamination Certificate
1999-07-12
2001-01-30
Look, Edward K. (Department: 3745)
Rotary kinetic fluid motors or pumps
With passage in blade, vane, shaft or rotary distributor...
C415S108000, C415S173100
Reexamination Certificate
active
06179557
ABSTRACT:
CROSS REFERENCE TO RELATED APPLICATIONS
Not applicable.
The present invention relates to turbine machinery, particularly of the kind utilised in gas turbine propulsion engines.
More specifically, the invention relates to the improved cooling of such devices, especially in those engines used for the propulsion of aircraft, though not restrictively so.
BACKGROUND OF THE INVENTION
Field of the Invention
It is the common practice to provide compressor air for the purpose of cooling a multiplicity of turbine machinery parts. Thus, it is know to provide compressor air to shrouds, which in situ, surround a stage of turbine blades, and thereby form an outer wall of an associated turbine annulus in which in operation, the stage of blades rotates.
A first drawback to the know system is that it necessitates the provision of duel airflows, one for cooling the downstream ends of the shrouds, and another for cooling the upstream ends thereof. This results in the use of a quantity of air which consequently cannot be used for combustion, and further results in a noticeable drop in engine efficiency.
A second drawback in known structures is that the air used for cooling the upstream ends of the shrouds, by virtue of structure, could not be finally ejected into the gas stream in the annulus, without disturbing the flow. This added further to efficiency losses.
SUMMARY OF THE INVENTION
The present invention seeks to provide an improved mode of cooling blade shrouds in turbine machinery.
According to the present invention, turbo machinery for a gas turbine engine comprises a turbine blade shroud capped by a cover which is in spaced relationship therewith intermediate the shroud ends, said space being connectable via the downstream end of said cover, to a cooling airflow supply from a compressor of a said engine, and connectable via said shroud near the shroud upstream end, to the gas annulus of a said engine so as to, on driven connection to a said engine, eject said cooling airflow when effected, into the gas annulus, in parallel with, and in the direction of, the gas flow therethrough.
REFERENCES:
patent: 3990807 (1976-11-01), Sifford
patent: 5267831 (1993-12-01), Damiral
patent: 5374161 (1994-12-01), Kelch
patent: 5584651 (1996-12-01), Pietraszkiewicz et al.
patent: 5649806 (1997-07-01), Scricca et al.
patent: 516322 (1992-12-01), None
patent: 709550 (1996-05-01), None
patent: 806815 (1958-12-01), None
patent: 1524956 (1978-09-01), None
patent: 2307520 (1997-05-01), None
Bhangu Jagnandan K
Dodd Alec G
Farkas & Manelli PLLC
Look Edward K.
Rolls-Royce plc
Taltavull W. Warren
Woo Richard
LandOfFree
Turbine cooling does not yet have a rating. At this time, there are no reviews or comments for this patent.
If you have personal experience with Turbine cooling, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Turbine cooling will most certainly appreciate the feedback.
Profile ID: LFUS-PAI-O-2486728