Abstract: A blade for a gas turbine is described, the blade comprising a trailing edge and a trailing edge cooling channel extending from a first upstream end to a second downstream end, in which the width of the trailing edge cooling channel in the direction perpendicular to the camber line of the blade varies and the narrowest width in the trailing edge cooling channel is at the first upstream end, so as to provide a blade where the trailing edge can be removed with a minimal change or no change in the cooling flow capacity through the trailing edge cooling channel. Related methods are also described.

Abstract: A mechanical component comprises an internal hollow space and a wall, the wall limiting the hollow space. The mechanical component further comprises a first channel extending inside the wall along a first direction and a second channel extending inside the wall in fluid communication with the internal hollow space and the first channel, serving as a feed channel. A cross-sectional dimension of the first channel is larger than a cross-sectional dimension of the feed channel, and the feed channel tangentially joins into the first channel. A third channel extends inside the wall in fluid communication with the first channel. The third channel extends inside the wall at least essentially parallel to a surface of the wall along at least a part of the extent of the wall in a second direction, and is a near wall cooling channel.

Abstract: Power systems are disclosed. The power system may include a turbine component of a gas turbine system, and a computing device(s) in communication with the power plant. The computing device(s) may be configured to control the power plant system by performing various processes including defining a turbine inlet temperature range for a combustion gas flowing through the turbine component of the gas turbine system. The turbine inlet temperature range may be based on a desired operational load for the power plant system. The processes performed by the computing device(s) may also include determining fuel and maintenance cost ranges based on the turbine inlet temperature range, calculating a desired turbine inlet temperature range for the combustion gas based on the determined fuel and maintenance cost range, and adjusting an actual turbine inlet temperature of the combustion gas to be within the calculated, desired turbine inlet temperature range.

Abstract: A mechanical component comprises an internal hollow space and a wall, the wall limiting the hollow space. The mechanical component further comprises a first channel extending inside the wall along a first direction and a second channel extending inside the wall in fluid communication with the internal hollow space and the first channel, serving as a feed channel. A cross-sectional dimension of the first channel is larger than a cross-sectional dimension of the feed channel, and the feed channel tangentially joins into the first channel. A third channel extends inside the wall in fluid communication with the first channel. The third channel extends inside the wall at least essentially parallel to a surface of the wall along at least a part of the extent of the wall in a second direction, and is a near wall cooling channel.

Abstract: Power systems are disclosed. The power system may include a turbine component of a gas turbine system, and a computing device(s) in communication with the power plant. The computing device(s) may be configured to control the power plant system by performing various processes including defining a turbine inlet temperature range for a combustion gas flowing through the turbine component of the gas turbine system. The turbine inlet temperature range may be based on a desired operational load for the power plant system. The processes performed by the computing device(s) may also include determining fuel and maintenance cost ranges based on the turbine inlet temperature range, calculating a desired turbine inlet temperature range for the combustion gas based on the determined fuel and maintenance cost range, and adjusting an actual turbine inlet temperature of the combustion gas to be within the calculated, desired turbine inlet temperature range.

Abstract: A self-adjusting device for controlling the clearance (C), especially in the radial direction, between rotating and stationary components of a thermally loaded turbo machine, changes clearance (C) in a linear and/or non-linear way during transition of the machine between standstill and steady-state operation. Simple and effective control can be achieved, even in the case of a nonlinear variation of the clearance during transitional operation, by the self-adjusting device including at least two different driving elements (A, B) to move the rotating and fixed components relative to each other in order to change the clearance (C) between them, and by the different driving elements (A, B) being configured to be activated at different times during the transition of the machine.

Abstract: A blade for a gas turbine is described, the blade comprising a trailing edge and a trailing edge cooling channel extending from a first upstream end to a second downstream end, in which the width of the trailing edge cooling channel in the direction perpendicular to the camber line of the blade varies and the narrowest width in the trailing edge cooling channel is at the first upstream end, so as to provide a blade where the trailing edge can be removed with a minimal change or no change in the cooling flow capacity through the trailing edge cooling channel. Related methods are also described.

Abstract: A rotating machine cooled by a cooling medium directed through the rotating machine in a main flow and a secondary flow includes a rotor. A stator includes a swirl passage configured to guide the secondary flow so as to be discharged from a pre-swirl nozzle. At least one control device includes a shape-memory alloy disposed in an area of the pre-swirl nozzle and is configured to control the secondary flow based on a temperature in an automated manner.

Abstract: A rotating machine cooled by a cooling medium directed through the rotating machine in a main flow and a secondary flow includes a rotor. A stator includes a swirl passage configured to guide the secondary flow so as to be discharged from a pre-swirl nozzle. At least one control device includes a shape-memory alloy disposed in an area of the pre-swirl nozzle and is configured to control the secondary flow based on a temperature in an automated manner.

Abstract: A sealing arrangement for sealing a gap (22) between two adjacent, thermally loaded components (14, 14?) of a thermal machine, especially a turbomachine or gas turbine, includes a seal (25) which is supported in a recess (23) which extends transversely to the gap (22) and traverses said gap (22). An efficient and simple improvement of the sealing arrangement is made by the seal (25) being formed at least partially of a shape memory alloy in such a way that, when a pre-specified temperature limit is exceeded, the seal changes its sealing behavior.

Abstract: A turbomachine which operates at enhanced operating temperatures includes a stationary component. A rotating component includes a clearance to avoid a rubbing contact between the stationary component and the rotating component, the clearance including a first value in a stationary state of the turbomachine and a second value in a steady-state operation of the machine, wherein during a transient operating phase between the stationary state and the steady-state operation, the clearance includes a value which traverses a curve having an extreme value on account of a different time variation of a rotational speed and a thermal expansion of different components. A compensating device includes a non-linear compensation mechanism configured to reduce or compensate the extreme value during the transient operating phase.

Abstract: A turbomachine which operates at enhanced operating temperatures includes a stationary component. A rotating component includes a clearance to avoid a rubbing contact between the stationary component and the rotating component, the clearance including a first value in a stationary state of the turbomachine and a second value in a steady-state operation of the machine, wherein during a transient operating phase between the stationary state and the steady-state operation, the clearance includes a value which traverses a curve having an extreme value on account of a different time variation of a rotational speed and a thermal expansion of different components. A compensating device includes a non-linear compensation mechanism configured to reduce or compensate the extreme value during the transient operating phase.

Abstract: A sealing arrangement for sealing a gap (22) between two adjacent, thermally loaded components (14, 14?) of a thermal machine, especially a turbomachine or gas turbine, includes a seal (25) which is supported in a recess (23) which extends transversely to the gap (22) and traverses said gap (22). An efficient and simple improvement of the sealing arrangement is made by the seal (25) being formed at least partially of a shape memory alloy in such a way that, when a pre-specified temperature limit is exceeded, the seal changes its sealing behavior.

Abstract: A rotating machine cooled by a cooling medium directed through the rotating machine in a main flow and a secondary flow includes a rotor. A stator includes a swirl passage configured to guide the secondary flow so as to be discharged from a pre-swirl nozzle. At least one control device includes a shape-memory alloy disposed in an area of the pre-swirl nozzle and is configured to control the secondary flow based on a temperature in an automated manner.