Abstract: The application relates to a method and a device for suppressing ice formation on intake structures of a compressor, particularly the compressor of a gas turbine. The technical aim of the present invention is to provide a method and a device for suppressing the formation of ice on said structures, which avoid the disadvantages of known solutions, such as a reduction of the performance of the gas turbine, and have a simple and broad applicability. According to the present invention the mechanical vibratory energy of said structures during operation is converted into electrical energy by a piezoelectric element, firmly applied to said structure, and in a connected electrical circuit the generated electrical energy is then converted into thermal energy by an ohmic resistor and this thermal energy is conducted to at least a portion of the structure for suppressing ice formation. Excess energy may be transmitted by a transmitter to other circuits in adjacent structures.

Abstract: A Helmholtz damper for a gas turbine is disclosed which includes a static resonator volume, which can be connected via a neck to an inner space of the gas turbine to damp pressure pulsations developing in the inner space. The static resonator volume can be changed in order to match resonances of the Helmholtz damper with the pressure pulsations. A simple and effective self-adjustment can be achieved via volume changing by at least one first element, which is exposed to a varying temperature within the gas turbine and undergoes a deformation, which depends on the varying temperature.

Abstract: A mechanical component for thermal turbo machinery, such as a steam or gas turbine, includes a base part and at least one additional device being mechanically coupled to the base part in order to influence the vibration characteristic of the base part during operation of the turbo machine. High-Cycle Fatigue at part-load can be reduced by enabling the mechanical coupling between the base part and the at least one additional device to change with the temperature of the at least one additional device.

Abstract: A mechanical fastening system for rotating or stationary components such as turbine or compressor blades on a rotor or a shaft or a casing, respectively, is disclosed. The system includes a circumferential mounting groove adapted for receiving root sections of the rotating or stationary components as well as intermediate fastening components for fixation of the components in equidistance positions. The intermediate fastening components comprise at least an upper platform and at least a side plate having a groove for mounting on said rotor. The intermediate fastening components are made of a plurality of distinct parts of different materials from which at least one clamping part is made of or comprises a shape memory alloy or similar material having a pseudo-elasticity 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.

Abstract: A component or coupon for use in a thermal machine under extreme thermal and mechanical conditions comprises an alloy material having a controllable grain size (d). A grain size distribution (d(X,Y,Z)) of the component or coupon corresponds to at least one of an expected temperature distribution (T(X,Y,Z)), an expected stress distribution (?(X,Y,Z)) and an expected strain distribution (?(X,Y,Z)), which vary with geometrical coordinates (X,Y,Z) of the component or coupon, such that a lifetime of the component or coupon is improved with respect to a similar component or coupon having a substantially uniform grain size.

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 thermally loaded, cooled component thermally coupled to a cooling system configured to receive a gaseous cooling introduced in a forced manner from outside that flows through the cooling system so as to absorb and transport heat away from the component as a result of thermal contact with the component. The component includes at least one Helmholtz resonator configured to improve thermal contact between the cooling medium and the component.

Abstract: The application relates to a method and a device for suppressing ice formation on intake structures of a compressor, particularly the compressor of a gas turbine. The technical aim of the present invention is to provide a method and a device for suppressing the formation of ice on said structures, which avoid the disadvantages of known solutions, such as a reduction of the performance of the gas turbine, and have a simple and broad applicability. According to the present invention the mechanical vibratory energy of said structures during operation is converted into electrical energy by a piezoelectric element, firmly applied to said structure, and in a connected electrical circuit the generated electrical energy is then converted into thermal energy by an ohmic resistor and this thermal energy is conducted to at least a portion of the structure for suppressing ice formation. Excess energy may be transmitted by a transmitter to other circuits in adjacent structures.

Abstract: In a method for influencing, in particular damping or suppressing, mechanical vibrations occurring during operation in a turbomachine blade (10), the mechanical vibratory energy of the turbomachine blade (10) is first converted into electrical energy and the electrical energy generated is then converted into heat loss. Effective damping which can be used especially simply and in a versatile way is achieved in that the piezoelectric effect is used in order to convert mechanical vibratory energy into electrical energy.

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 component for use in an engine in which the component is subjected to at least one of a high temperature, a corrosive atmosphere, an oxidizing atmosphere, a high mechanical load, a cyclic thermal load and transient conditions such that the component is prone to crack formation and propagation. At least one base material includes a self healing system in a form of an added active phase, the self healing system including at least one of a melting point depressant and a substance having a softening or a melting point below or within a range of an operating temperature of the component.

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.

Abstract: In a method for influencing, in particular damping or suppressing, mechanical vibrations occurring during operation in a turbomachine blade (10), the mechanical vibratory energy of the turbomachine blade (10) is first converted into electrical energy and the electrical energy generated is then converted into heat loss. Effective damping which can be used especially simply and in a versatile way is achieved in that the piezoelectric effect is used in order to convert mechanical vibratory energy into electrical energy.

Abstract: A thermally loaded, cooled component thermally coupled to a cooling system configured to receive a gaseous cooling introduced in a forced manner from outside that flows through the cooling system so as to absorb and transport heat away from the component as a result of thermal contact with the component. The component includes at least one Helmholtz resonator configured to improve thermal contact between the cooling medium and the component.