Rotary kinetic fluid motors or pumps – With passage in blade – vane – shaft or rotary distributor...
Patent
1991-05-20
1992-12-08
Kwon, John T.
Rotary kinetic fluid motors or pumps
With passage in blade, vane, shaft or rotary distributor...
415116, F01D 518
Patent
active
051692872
ABSTRACT:
To cool the shroud in the high pressure turbine section of a gas turbine engine, high pressure cooling air is directed in metered flow to baffle plenums and thence through baffle perforations to impingement cool the shroud rails and back surface. Impingement cooling air then flows through elongated, convection cooling passages in the shroud and exits to flow along the shroud front surface with the main gas stream to provide film cooling. The baffle perforations and the convection cooling passages are interactively located to achieve maximum cooling benefit and highly efficient cooling air utilization.
REFERENCES:
patent: 3583824 (1971-06-01), Smuland
patent: 3628880 (1971-12-01), Smuland
patent: 3800864 (1974-04-01), Hauser et al.
patent: 3844343 (1974-10-01), Burggarf
patent: 3975901 (1976-08-01), Hallinger et al.
patent: 4017213 (1977-04-01), Przirembel
patent: 4222707 (1980-09-01), Drouet et al.
patent: 4303371 (1981-12-01), Eckert
patent: 4317646 (1982-03-01), Steel et al.
patent: 4526226 (1985-07-01), Hsia et al.
patent: 4551064 (1985-11-01), Pask
patent: 4573865 (1986-03-01), Hsia et al.
patent: 4693667 (1987-09-01), Lenz et al.
patent: 4820116 (1989-04-01), Hovan et al.
patent: 5039562 (1991-08-01), Liang
patent: 5048288 (1991-09-01), Bessette et al.
Albers Robert J.
Brainch Gulcharan S.
Hess John R.
Plemmons Larry W.
Proctor Robert
General Electric Company
Kwon John T.
Rafter John R.
Squillaro Jerome C.
LandOfFree
Shroud cooling assembly for gas turbine engine does not yet have a rating. At this time, there are no reviews or comments for this patent.
If you have personal experience with Shroud cooling assembly for gas turbine engine, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Shroud cooling assembly for gas turbine engine will most certainly appreciate the feedback.
Profile ID: LFUS-PAI-O-957401