Power plants – Combustion products used as motive fluid – Combustion products generator
Reexamination Certificate
1998-12-18
2001-09-11
Kim, Ted (Department: 3746)
Power plants
Combustion products used as motive fluid
Combustion products generator
C060S757000, C060S758000, C060S750000
Reexamination Certificate
active
06286317
ABSTRACT:
BACKGROUND OF THE INVENTION
1. Field of the Invention
The present invention relates to a liner for a gas turbine engine combustor having a trapped vortex cavity and, more particularly, to an annular cooling nugget connecting a cavity liner section with a downstream liner section.
2. Description of Related Art
Advanced aircraft gas turbine engine technology requirements are driving the combustors therein to be shorter in length, have higher performance levels over wider operating ranges, and produce lower exhaust pollutant emission levels. One example of a combustor designed to achieve these objectives is disclosed in U.S. Pat. No. 5,619,855 to Burrus. As seen therein, the Burrus combustor is able to operate efficiently at inlet air flows having a high subsonic Mach Number. This stems in part from a dome inlet module which allows air to flow freely from an upstream compressor to the combustion chamber, with fuel being injected into the flow passage. The combustor also has inner and outer liners attached to the dome inlet module which include upstream cavity portions for creating a trapped vortex of fuel and air therein, as well as downstream portions extending to the turbine nozzle.
It has been found in the aforementioned Burrus combustor that hot gases from the cavity combustion zones, having high temperatures and moderately high velocities, impinge on a corner junction where the cavity section of the respective liner joins the remaining downstream liner section. This results in high heat loads on such junction of the liner. While a cooling passage is disclosed in the '855 patent at the upstream end of the downstream liner section to initiate cooling flow along the surface thereof, additional cooling is required at both the corner junction itself and along the rear surface of the cavity liner section. Moreover, the corner junction of the cavity liner section and the downstream liner section is challenged structurally and measures which would also strengthen this area are likewise needed.
Accordingly, it would be desirable for a liner to be developed in which the junction between a cavity liner section and a downstream liner section would have greater structural stability. Further, it would be desirable if such liner would provide greater cooling at this location and along the rear portion of the cavity liner section.
SUMMARY OF THE INVENTION
In accordance with one aspect of the present invention, a liner for a gas turbine engine combustor is disclosed as including an upstream section, a downstream section oriented at an angle to the upstream liner section, and an annular cooling nugget joining the upstream and downstream liner sections for providing mechanical stiffness at a junction of the upstream and downstream liner sections. The cooling nugget further includes a first portion connected to the upstream liner section, a second portion connected to the downstream liner section, and a third portion joining the first and second cooling nugget portions at a first end, the third cooling nugget portion extending radially from the first end, wherein the cooling nugget is in flow communication with a cool air supply and is configured to provide a starter film of cooling air along respective surfaces of the upstream liner section and the downstream liner section.
In accordance with a second aspect of the present invention, a cooling nugget for joining adjacent sections of a gas turbine engine liner is disclosed, wherein the liner sections are oriented at an angle with respect to each other. The cooling nugget includes a first portion connected to an upstream liner section, a second portion connected to a downstream liner section, and a third portion joining the first and second portions at a first end. The third portion extends radially from the first end, wherein the third portion is in flow communication with a cool air supply and is configured to provide a starter film of cooling air along respective surfaces of the upstream liner section and the downstream liner section. The cooling nugget third portion further includes a first flange portion connected to a second end of the third portion, the first flange portion being spaced from and oriented parallel to the upstream liner section, as well as a second flange portion connected to the second end of the third portion, the second flange portion being spaced from and oriented parallel to the downstream liner section.
In accordance with a third aspect of the present invention, an annular cooling nugget for joining adjacent sections of a gas turbine engine liner is disclosed, wherein the liner sections are oriented at an angle with respect to each other. The cooling nugget includes a first portion connected to an upstream liner section, a second portion connected to a downstream liner section, and a third portion joining the first and second portions at a first end. The third portion extends radially from the first end and has a plurality of spaced cooling passages incorporated therein, wherein the cooling nugget third portion is in flow communication with a cool air supply and is configured so as to provide cooling air at the junction of the upstream liner section and the downstream liner section.
REFERENCES:
patent: 3430443 (1969-03-01), Richardson et al.
patent: 3952503 (1976-04-01), Fox et al.
patent: 4051670 (1977-10-01), Pierce
patent: 4104874 (1978-08-01), Caruel et al.
patent: 4365477 (1982-12-01), Pearce
patent: 4749029 (1988-06-01), Becker et al.
patent: 5129447 (1992-07-01), Hamner
patent: 5265425 (1993-11-01), Howell
patent: 5319923 (1994-06-01), Leonard et al.
patent: 5619855 (1997-04-01), Burrus
patent: 5791148 (1998-08-01), Burrus
patent: 2073396 (1981-10-01), None
patent: 2099978 (1982-12-01), None
Burrus David L.
Johnson Arthur W.
Moertle George E.
General Electric Company
Hess Andrew C.
Kim Ted
Young Rodney M.
LandOfFree
Cooling nugget for a liner of a gas turbine engine combustor... does not yet have a rating. At this time, there are no reviews or comments for this patent.
If you have personal experience with Cooling nugget for a liner of a gas turbine engine combustor..., we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Cooling nugget for a liner of a gas turbine engine combustor... will most certainly appreciate the feedback.
Profile ID: LFUS-PAI-O-2478995