A system and method for mitigating thermal loading between engine exhaust structures having different coefficients of thermal expansion. The engine exhaust structure comprises a metallic duct portion, a ceramic duct portion, and a double bipod fitting joining the metallic duct portion to the ceramic duct portion. The double bipod fitting is capable of flexing and taking up the thermal expansion differences between the joined metallic and ceramic ducts across the full temperature spectrum that an engine exhaust structure will experience in service.

One or more cooling systems for ventilating a turbine and rotary shaft of a gas turbine system is provided. The gas turbine system includes a gas turbine engine and a turbine exhaust collector in separate enclosures. A first cooling system includes an educator that sucks exhaust gas through a diffuser and directs it out of the turbine exhaust collector enclosure based on suction pressure created from the high velocity of exhaust gas. A second cooling system include struts that enable the exhaust gas to flow from the diffusers to a ventilation flow stack. A third cooling system includes exhaust gas sucked from an opening to a top duct based on suction pressure created from the rotation of the rotary shaft disposed about a coupling. A guideway associated with the third cooling system also directs the exhaust gas to flow to the top duct. These cooling systems are designed to increase the efficiency of ventilating the turbine and rotary shaft, prevent misalignments of the rotary shaft, which may result in thermal stresses, and allow the use of the gas turbine systems in higher ambient temperature environments.

One or more cooling systems for ventilating a turbine and rotary shaft of a gas turbine system is provided. The gas turbine system includes a gas turbine engine and a turbine exhaust collector in separate enclosures. A first cooling system includes an educator that sucks exhaust gas through a diffuser and directs it out of the turbine exhaust collector enclosure based on suction pressure created from the high velocity of exhaust gas. A second cooling system include struts that enable the exhaust gas to flow from the diffusers to a ventilation flow stack. A third cooling system includes exhaust gas sucked from an opening to a top duct based on suction pressure created from the rotation of the rotary shaft disposed about a coupling. A guideway associated with the third cooling system also directs the exhaust gas to flow to the top duct. These cooling systems are designed to increase the efficiency of ventilating the turbine and rotary shaft, prevent misalignments of the rotary shaft, which may result in thermal stresses, and allow the use of the gas turbine systems in higher ambient temperature environments.

An exhaust hood (Ec) of the present invention is provided with an inner casing (21), an outer casing (30), and a diffuser (26). The inner casing (21) surrounds a rotor from the outside in a radial direction, and forms a first space (21s) in which a fluid flows in an axial direction (Da) between the rotor and the inner casing (21). The diffuser (26) is provided with a bearing cone (29) that has a diameter that gradually widens moving towards an axial downstream side (Dad) and forms a cylindrical shape extending to the axial downstream side (Dad) to be continuous with the outer circumferential surface of a rotor shaft that forms the first space (21s). An end edge (29a) on the axial downstream side (Dad) of the bearing cone (29) forms an oval shape in which, in a direction orthogonal to an axial line (Ar), a distance (R2an) between the axial line (Ar) and a second cone end part (29ab) of a second side (Dan) is greater than a distance (R2ex) between the axial line (Ar) and a first cone end part (29aa) of a first side (Dex).

An exhaust hood (Ec) of the present invention is provided with an inner casing (21), an outer casing (30), and a diffuser (26). The inner casing (21) surrounds a rotor from the outside in a radial direction, and forms a first space (21s) in which a fluid flows in an axial direction (Da) between the rotor and the inner casing (21). The diffuser (26) is provided with a bearing cone (29) that has a diameter that gradually widens moving towards an axial downstream side (Dad) and forms a cylindrical shape extending to the axial downstream side (Dad) to be continuous with the outer circumferential surface of a rotor shaft that forms the first space (21s). An end edge (29a) on the axial downstream side (Dad) of the bearing cone (29) forms an oval shape in which, in a direction orthogonal to an axial line (Ar), a distance (R2an) between the axial line (Ar) and a second cone end part (29ab) of a second side (Dan) is greater than a distance (R2ex) between the axial line (Ar) and a first cone end part (29aa) of a first side (Dex).

A system includes a gas turbine engine configured to combust an oxidant and a fuel to generate an exhaust gas, a catalyst bed configured to treat a portion of the exhaust gas from the gas turbine engine to generate a treated exhaust gas, a differential temperature monitor configured to monitor a differential temperature between a first temperature of the portion of exhaust gas upstream of the catalyst bed and a second temperature of the treated exhaust gas downstream of the catalyst bed, and an oxidant-to-fuel ratio system configured to adjust a parameter to maintain an efficacy of the catalyst bed based at least in part on the differential temperature in order to maintain a target equivalence ratio.

A system includes a gas turbine engine configured to combust an oxidant and a fuel to generate an exhaust gas, a catalyst bed configured to treat a portion of the exhaust gas from the gas turbine engine to generate a treated exhaust gas, a differential temperature monitor configured to monitor a differential temperature between a first temperature of the portion of exhaust gas upstream of the catalyst bed and a second temperature of the treated exhaust gas downstream of the catalyst bed, and an oxidant-to-fuel ratio system configured to adjust a parameter to maintain an efficacy of the catalyst bed based at least in part on the differential temperature in order to maintain a target equivalence ratio.

A tuned mass damper for reducing vibration on a component includes a shaft connector member configured to be coupled to the component and a cable termination member. The tuned mass damper also includes at least one cable coupled to the shaft connector member and to the cable termination member such that vibration of the component is transferred to the at least one cable via the shaft connector member and increased or decreased by the at least one cable.

A gas turbine including a turbine driven by a combustion gas, a gas turbine casing that includes an exhaust casing having an inner tube and an outer tube, a bearing that rotatably supports a shaft of the turbine, a bearing casing that holds the bearing, a support leg that supports the gas turbine casing, struts that connect the inner tube and the outer tube, and a first support and a second support that support the bearing casing on the inner tube. The first support is located on a side same as the support leg relative to the struts in a flow direction of the combustion gas. The struts are located between the first support and the second support. The first support is fixed to the inner tube and the bearing casing. The second support is fixed to the inner tube and is in slidable contact with the bearing casing.

A connecting structure (10) for load transfer, in particular in a gas turbine (1), including a strut (20) and at least one wall element (30) is provided. The strut (20) at one end is integrally joined to the wall element (30), and the strut (20) and the wall element (30) are enclosed by a fillet (40), at least in areas, and integrally joined to same. An elastic deformation of the involved elements of the structure during the load transfer and/or load absorption is improved in that a root section (50) that is formed by a ridge (56) and that extends from the strut (20) to the wall element (30) is situated on the fillet (40).