Abstract: A burner for a gas combustor and a method of operating the burner are disclosed. The burner includes a front surface area divided into a plurality of subareas and inlets arranged on the front surface area such that each subarea is encircled by at least four inlets and such that during operation of the burner, a gas recirculation in the combustor is facilitated corresponding to each subarea.

Abstract: The invention relates to a cooling channel for a component conveying hot gas for the purposes of conveying a coolant along a direction of flow with a downstream and an upstream side, with a plurality of inlet apertures for a coolant, with a number of inlet apertures that vary their configuration at least partly among themselves is arranged at least in one section of the cooling channel. As a result, the heat-transfer coefficient is substantially increased at points particularly requiring cooling and therefore the cooling is substantially improved. The cooling channel is characterized by a particularly low pressure loss. Furthermore, a combustion chamber with a cooling channel of this type is specified.

Abstract: A burner for a gas combustor and a method of operating the burner are disclosed. The burner includes a front surface area divided into a plurality of subareas and inlets arranged on the front surface area such that each subarea is encircled by at least four inlets and such that during operation of the burner, a gas recirculation in the combustor is facilitated corresponding to each subarea.

Abstract: A transition duct support system for a transition duct that channels hot gases from a combustor exit to a gas turbine inlet of a turbine engine. The transition duct support system includes a transition support frame formed from a body positioned around a transition duct body at an outlet transition section. The transition support frame may include a first inner surface aligned with and positioned proximate to portion of the outlet transition section that is positioned at an oblique angle relative to the outer wall of the transition duct body to limit linear movement of the transition duct body in a first direction. The transition support frame may also include a second inner surface positioned at an oblique angle to limit linear movement of the transition duct body in a second direction opposite the first direction.

Abstract: A transition duct support system for a transition duct that channels hot gases from a combustor exit to a gas turbine inlet of a turbine engine. The transition duct support system includes a transition support frame formed from a body positioned around a transition duct body at an outlet transition section. The transition support frame may include a first inner surface aligned with and positioned proximate to portion of the outlet transition section that is positioned at an oblique angle relative to the outer wall of the transition duct body to limit linear movement of the transition duct body in a first direction. The transition support frame may also include a second inner surface positioned at an oblique angle to limit linear movement of the transition duct body in a second direction opposite the first direction.

Abstract: Embodiments of a transition (400) of the present invention comprise a cooling channel (20, 30, 410) defined in part by an outer wall (23) and an inner wall (24). The cooling channel (20, 30, 410) also comprises lateral side walls (33, 34). Two or more subdomains (AA, BB, A, B1, B2, C1, C2, D) of impingement jets (25, 35) are provided through the outer wall (23), and one or more metering outlets (26, 36, 37, 38) is provided through the inner wall (24), all communicating with a respective channel (20, 30, 410). The impingement jets of each respective subdomain are designed to supply cooling fluid to one of the one or more metering outlets.

Abstract: A transition (200) for a gas turbine engine (100) comprises a transition wall (201) comprising cooling channels (213L, 213R, 223L, 223R) that are adapted to pass a cooling fluid, such as compressed air from a compressor (102) during operation of the gas turbine engine (100) so as to cool combusted hot gases passing through the transition (200). For each cooling channel (213L, 213R, 223L, 223R), respective entry ports (212L, 212L, 222L, 222R) and exit ports (214L, 214R, 224L, 224R) are arranged so as to obtain a performance improvement based upon pressure differentials between the respective entry and exit ports. In various embodiments, a scoop (220) is associated with an entry port (222L, 222R) so as to establish a more elevated pressure differential in the respective cooling channel (223L, 223R). An entry port (330a-h) may be positioned offset relative to a lower-positioned exit port (340a-h) so as to so minimize or eliminate intake of heated airflow from a respective nearby exit port (340a-h).

Abstract: A transition duct having an inlet opening and an outlet opening and a body portion extending between the inlet and outlet openings at respective inlet and outlet ends. The inlet opening defines a generally circular cross-section for the body portion and has a geometric center, and the outlet opening defines a generally rectangular arc-like cross-section. The body portion has an internal profile substantially in accordance with coordinate values X, Y and Z at an angle ?, as set forth in Table 1, where each of the X, Y and Z coordinate values are taken at a sweep angle ? passing through the section origin and measured from a first plane defined by the inlet end and increasing toward a second plane defined by the outlet end.

Abstract: A pilot nozzle heat shield includes a body having a first end for receiving a pilot nozzle and a second end including a flow tip. The body includes a plurality of internal turbulators circumferentially disposed about the internal peripheral surface of the body. The flow tip includes a proximal periphery and a distal periphery. A plurality of flow ports are circumferentially spaced about the proximal periphery of the flow tip. The flow tip includes a plurality of slots. Each slot extends distally from one of the flow ports to the distal periphery of the flow tip, which defines an aperture. The plurality of slots define a plurality of tangs; each tang is defined between a pair of neighboring slots. A plurality of turbulators can be disposed about the inner peripheral surface of the heat shield body at the tangs.

Abstract: A pilot nozzle heat shield includes a body having a first end for receiving a pilot nozzle and a second end including a flow tip. The body includes a plurality of internal turbulators circumferentially disposed about the internal peripheral surface of the body. The flow tip includes a proximal periphery and a distal periphery. A plurality of flow ports are circumferentially spaced about the proximal periphery of the flow tip. The flow tip includes a plurality of slots. Each slot extends distally from one of the flow ports to the distal periphery of the flow tip, which defines an aperture. The plurality of slots define a plurality of tangs; each tang is defined between a pair of neighboring slots. A plurality of turbulators can be disposed about the inner peripheral surface of the heat shield body at the tangs.

Abstract: The invention relates to a cooling channel for a component conveying hot gas for the purposes of conveying a coolant along a direction of flow with a dowrnstream and an upstream side, with a plurality of inlet apertures for a coolant, with a number of inlet apertures that vary their configuration at least partly among themselves is arranged at least in one section of the cooling channel. As a result, the heat-transfer coefficient is substantially increased at points particularly requiring cooling and therefore the cooling is substantially improved. The cooling channel is characterized by a particularly low pressure loss.

Abstract: A plenum (210) in a gas turbine engine mid-frame section (200) comprises one or more annular flow splitters (240) spaced from an inboard annular wall (232) that partition air flow flowing from a compressor into two or more portions of flow having different vectors. This provides for an improved balancing between supplying air to compression chamber intakes more directly and to transitions to aid in convective cooling. When an annular diffuser (202) is spaced between the compressor and the plenum (210), the flow splitters (240) may provide an additional diffusion action. When no annular diffuser is so provided, the flow splitters (452, 454, 456) are effective to diffuse the air flow. Embodiments include those in which an annular diffuser (304) is relatively shorter and there is a longer axial expanse in the plenum (320) for flow splitters (350, 352, 354, 356).

Abstract: Embodiments of a transition (400) of the present invention comprise a cooling channel (20, 30, 410) defined in part by an outer wall (23) and an inner wall (24). The cooling channel (20, 30, 410) also comprises lateral side walls (33, 34). Two or more subdomains (AA, BB, A, B1, B2, C1, C2, D) of impingement jets (25, 35) are provided through the outer wall (23), and one or more metering outlets (26. 36, 37, 38) is provided through the inner wall (24), all communicating with a respective channel (20, 30, 410). The impingement jets of each respective subdomain are designed to supply cooling fluid to one of the one or more metering outlets. Further to the impingement jets (25, 35) their size, shape, spacing, and arrangement with regard to the metering outlet (26.

Abstract: A transition duct support system for a transition duct that channels hot gases from a combustor exit to a gas turbine inlet of a turbine engine. The transition duct support system includes a transition support frame formed from a body positioned around a transition duct body at an outlet transition section. The transition support frame may include a first inner surface aligned with and positioned proximate to portion of the outlet transition section that is positioned at an oblique angle relative to the outer wall of the transition duct body to limit linear movement of the transition duct body in a first direction. The transition support frame may also include a second inner surface positioned at an oblique angle to limit linear movement of the transition duct body in a second direction opposite the first direction.

Abstract: A transition duct having an inlet opening and an outlet opening and a body portion extending between the inlet and outlet openings at respective inlet and outlet ends. The inlet opening defines a generally circular cross-section for the body portion and has a geometric center, and the outlet opening defines a generally rectangular arc-like cross-section. The body portion has an internal profile substantially in accordance with coordinate values X, Y and Z at an angle ?, as set forth in Table 1, where each of the X, Y and Z coordinate values are taken at a sweep angle ? passing through the section origin and measured from a first plane defined by the inlet end and increasing toward a second plane defined by the outlet end.

Abstract: A plenum (210) in a gas turbine engine mid-frame section (200) comprises one or more annular flow splitters (240) spaced from an inboard annular wall (232) that partition air flow flowing from a compressor into two or more portions of flow having different vectors. This provides for an improved balancing between supplying air to compression chamber intakes more directly and to transitions to aid in convective cooling. When an annular diffuser (202) is spaced between the compressor and the plenum (210), the flow splitters (240) may provide an additional diffusion action. When no annular diffuser is so provided, the flow splitters (452, 454, 456) are effective to diffuse the air flow. Embodiments include those in which an annular diffuser (304) is relatively shorter and there is a longer axial expanse in the plenum (320) for flow splitters (350, 352, 354, 356).

Abstract: A gas turbine combustor (10) having a first grouping (64) of pre-mix burners (12, 12?, 12?) having mixing passages (36) that are geometrically different than the mixing passages (38) of a second grouping (66) of pre-mix burners (14, 14?, 14?). The aerodynamic differences created by these geometric differences provide a degree of control over combustion properties of the respective flames (44, 46) produced in a downstream combustion chamber (40) when the two groupings of burners are fueled by separate fuel stages (52, 54). The geometric difference between the fuel passages of the two groupings may be outlet diameter, slope of convergence of the passage diameter, or outlet contour. The fuel injection regions (16, 18) of all of the burners may be identical to reduce cost and inventory complexity. The burners may be arranged in a ring (60) with a center pre-mix burner (68) being identical to burners of either of the groupings.

Abstract: A gas turbine combustor (10) having a first grouping (64) of pre-mix burners (12, 12′, 12″) having mixing passages (36) that are geometrically different than the mixing passages (38) of a second grouping (66) of pre-mix burners (14, 14′, 14″). The aerodynamic differences created by these geometric differences provide a degree of control over combustion properties of the respective flames (44, 46) produced in a downstream combustion chamber (40) when the two groupings of burners are fueled by separate fuel stages (52, 54). The geometric difference between the fuel passages of the two groupings may be outlet diameter, slope of convergence of the passage diameter, or outlet contour. The fuel injection regions (16, 18) of all of the burners may be identical to reduce cost and inventory complexity. The burners may be arranged in a ring (60) with a center pre-mix burner (68) being identical to burners of either of the groupings.

Abstract: A bird cage (20) includes a centrally disposed bird receiving structure (30) and inwardly sloping sides (28) which in combination cause birds to face inward and thereby defecate away from the bird receiving structure. These features make the cleaning of the bird cage easier. In a preferred embodiment, the bird cage also includes a removable top portion (24) which is selectively connected to a bottom portion (22). Since the top portion can be removed from the bottom portion, cleaning of the bird cage is simplified. In a preferred embodiment, the bird cage does not include a conventional door.