| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 060760000 | Air outside liner flows counter to combustion products flow within liner | 11 |
| 20080276619 | Impingement jets coupled to cooling channels for transition cooling - Embodiments of a transition ( | 11-13-2008 |
| 20100005805 | FLOW SLEEVE WITH TABBED DIRECT COMBUSTION LINER COOLING AIR - A combustion duct for a gas turbine engine has a combustion liner to receive products of combustion, and deliver the products of combustion downstream toward a turbine rotor. An outer housing is positioned radially outwardly of the combustion liner. A flow sleeve is positioned radially intermediate the outer housing and the combustion liner. A chamber radially outwardly of the flow sleeve receives cooling air. A plurality of holes through the flow sleeve deliver cooling air from the chamber against an outer periphery of the combustion liner. A plurality of tabs are associated with at least some of the holes in the flow sleeve. The tabs are positioned to extend radially inwardly on a downstream side of the holes. | 01-14-2010 |
| 20100031665 | FLOW SLEEVE IMPINGEMENT COOLING USING A PLENUM RING - A combustor assembly for a turbine engine includes a combustor liner, a flow sleeve and a plenum ring. The flow sleeve surrounds the combustor liner to form an annulus radially between the combustor liner and the flow sleeve. The flow sleeve has a plurality of rows of cooling holes. The plenum ring radially surrounds the combustor liner in the annulus. The plenum ring has a plurality of bypass tubes for directing axial air flow and radial flow chambers for directing radial air flow. | 02-11-2010 |
| 20100031666 | FLOW SLEEVE IMPINGEMENT COOLILNG BAFFLES - A combustor assembly for a turbine engine includes a combustor liner, a flow sleeve and a baffle ring. The flow sleeve surrounds the combustor liner. An annulus is formed between the flow sleeve and the combustor liner. A plurality of row of cooling holes are formed in the flow sleeve. The baffle ring radially surrounds the combustor liner and is located in the annulus. | 02-11-2010 |
| 20100064693 | COMBUSTOR ASSEMBLY COMPRISING A COMBUSTOR DEVICE, A TRANSITION DUCT AND A FLOW CONDITIONER - A combustor assembly in a gas turbine engine is provided. The combustor assembly may comprise a combustor device coupled to a main casing, a transition duct and a flow conditioner. The combustor device may comprise a liner having inlet and outlet portions and a burner assembly positioned adjacent to the liner inlet. The transition duct may comprise a conduit having inlet and outlet sections. The inlet section may be associated with the liner outlet portion. The flow conditioner may be associated with the main casing and the transition duct conduit for supporting the conduit inlet section. | 03-18-2010 |
| 20100180602 | COMBUSTOR ASSEMBLY AND CAP FOR A TURBINE ENGINE - A combustor assembly for a turbine engine includes a cap assembly which gradually increases the volume of compressed air provided to the combustor assembly, and which slows the compressed air in a controlled manner before delivering the compressed air into a combustor area. The cap assembly includes inner and outer sleeves which are mounted in a concentric fashion. The annular space formed between the inner and outer sleeves gradually increases from an aft end to a forward end. A stepped portion is formed on the inner sleeve of the cap assembly, and this stepped portion is joined to a corresponding combustor liner. | 07-22-2010 |
| 20100223931 | PATTERN COOLED COMBUSTOR LINER - A system, in one embodiment, includes a turbine combustor liner. The combustor liner includes a patterned surface at a downstream end portion relative to a downstream direction of combustion along a longitudinal axis of the turbine combustor liner. The patterned surface includes a plurality of discrete protrusions in both axial and circumferential directions about the downstream end portion relative to the longitudinal axis of the turbine combustion liner. | 09-09-2010 |
| 20100251723 | THIMBLE, SLEEVE, AND METHOD FOR COOLING A COMBUSTOR ASSEMBLY - A method for cooling a combustor assembly having a cooling passage. The method includes providing at least one thimble including an inner surface that defines a first opening, a second opening that is downstream from the first opening, and a flow channel that extends between the first opening and the second opening. The flow channel has a converging portion and a recovery portion that is downstream from the converging portion. The method also includes inserting the at least one thimble into at least one inlet that is defined in at least one sleeve such that cooling air is discharged from the flow channel into the cooling passage. | 10-07-2010 |
| 20120198855 | METHOD AND APPARATUS FOR COOLING COMBUSTOR LINER IN COMBUSTOR - A method and apparatus for cooling a combustor liner in a combustor are disclosed. In one embodiment, a combustor is disclosed. The combustor includes a transition piece, and an impingement sleeve at least partially surrounding the transition piece and at least partially defining a generally annular flow path therebetween. The combustor further includes an injection sleeve mounted to one of the transition piece or the impingement sleeve and positioned radially outward of the impingement sleeve, the injection sleeve at least partially defining a flow channel configured to flow working fluid to the flow path. In another embodiment, a method for cooling a combustor liner in a combustor is disclosed. The method includes flowing a working fluid through a flow channel at least partially defined by an injection sleeve, and exhausting the working fluid from the flow channel into a flow path adjacent the combustor liner. | 08-09-2012 |
| 20120210720 | COMBUSTOR ASSEMBLY FOR USE IN A TURBINE ENGINE AND METHODS OF FABRICATING SAME - A combustor assembly that includes a casing that includes a plenum, a combustor liner positioned within the plenum and defining a combustion chamber there within, and a transition piece that includes a forward portion that is coupled to the combustion liner and an aft portion that extends from the forward portion. The aft portion includes a transition piece frame. The transition piece frame includes an upstream surface, a downstream surface, and a radially inner surface extending between the upstream and downstream surfaces. The radially inner surface includes a leading edge that extends between the radially inner surface and the upstream surface. A plurality of first cooling passages extend from the upstream surface to the downstream surface. Each of the first cooling passages is oriented obliquely with respect to the leading edge from the upstream surface towards the downstream surface. | 08-23-2012 |
| 20140230442 | Gas Turbine Combustor Equipped with Heat-Transfer Device - An object of the present invention is to provide a gas turbine combustor that can suppress an increase in pressure loss while improving product reliability. | 08-21-2014 |
