Abstract: A method of cleaning a component includes providing the component following the operation of the component in a high temperature environment, the component including a thermal barrier coating (TBC), cleaning the TBC of the component using a sponge jet blasting process, and measuring a cleaned thickness of the TBC to verify that the cleaned thickness exceeds a predetermined minimum value that will allow the return of the component to the high temperature environment.

Abstract: A method of cleaning a component includes providing the component following the operation of the component in a high temperature environment, the component including a thermal barrier coating (TBC), cleaning the TBC of the component using a sponge jet blasting process, and measuring a cleaned thickness of the TBC to verify that the cleaned thickness exceeds a predetermined minimum value that will allow the return of the component to the high temperature environment.

Abstract: Turbine blade-tip clearance is measured in a fully assembled turbine casing by mounting a probe tip of a non-contact displacement probe in an inspection port of a vane cavity at a known distance relative to the inner circumferential surface of the corresponding ring segment. The displacement probe generates displacement samples that are indicative of probe tip distance from the turbine blade tip. Variations in probe distance data are recorded as the blade circumferentially sweeps the turbine casing. A data processing system correlates the distance data with localized blade-tip clearance gap. In some embodiments, blade rotational position data are collected by a rotational position sensor. In those embodiments, the data processing system correlates the distance and rotational position data with localized blade tip gap at angular positions about the turbine casing circumference.

Abstract: Turbine blade-tip clearance is measured in a fully assembled turbine casing by mounting a probe tip of a non-contact displacement probe in an inspection port of a vane cavity at a known distance relative to the inner circumferential surface of the corresponding ring segment. The displacement probe generates displacement samples that are indicative of probe tip distance from the turbine blade tip. Variations in probe distance data are recorded as the blade circumferentially sweeps the turbine casing. A data processing system correlates the distance data with localized blade-tip clearance gap. In some embodiments, blade rotational position data are collected by a rotational position sensor. In those embodiments, the data processing system correlates the distance and rotational position data with localized blade tip gap at angular positions about the turbine casing circumference.

Abstract: Turbine blade tip clearance is measured in a fully assembled turbine casing by mounting a non-contact displacement probe or sensor on a turbine blade that generates data indicative of sensor distance from the turbine casing that circumferentially surrounds the blade. The sensor is mounted on the blade with a sensor fixture, which includes a clamping mechanism and a sensor retention mechanism that retains and calibrates the sensor by selective movement of the sensor relative to the retention mechanism. Variations in sensor distance data are recorded when the turbine is operated in turning gear mode. Blade rotational position data are collected by a rotational position sensor. A data processing system correlates the distance and rotational position data with localized blade tip gap at angular positions about the turbine casing circumference. This method and apparatus facilitate assessment of turbine casing deformation impact on blade tip clearance and rotor/casing alignment.

Abstract: Turbine blade tip clearance is measured in a fully assembled turbine casing by mounting a non-contact displacement probe or sensor on a turbine blade that generates data indicative of sensor distance from the turbine casing that circumferentially surrounds the blade. The sensor is mounted on the blade with a sensor fixture, which includes a clamping mechanism and a sensor retention mechanism that retains and calibrates the sensor by selective movement of the sensor relative to the retention mechanism. Variations in sensor distance data are recorded when the turbine is operated in turning gear mode. Blade rotational position data are collected by a rotational position sensor. A data processing system correlates the distance and rotational position data with localized blade tip gap at angular positions about the turbine casing circumference. This method and apparatus facilitate assessment of turbine casing deformation impact on blade tip clearance and rotor/casing alignment.

Abstract: An apparatus for dislodging stuck blades in a turbine engine. The apparatus includes a housing, cam structure, and impact structure. The housing is capable of being temporarily secured to a blade disc structure adjacent to a stuck blade to be dislodged. The cam structure is associated with the housing and is adapted to receive an input torque that rotates the cam structure, the cam structure capable of translating the input torque into an impact force, the impact force including a component in a desired direction. The impact structure is associated with the housing and is capable of receiving the impact force from the cam structure and exerting the impact force on a root area of the stuck blade for dislodging the stuck blade from the blade disc structure non-destructively.

Abstract: A blade closing key system includes a first key piece and a second key piece. The first key piece includes a first finger and an elongated alignment plate. The second key piece includes a second finger and a key slot. The key pieces are installed in a cavity collectively formed by a notch in a blade root and a slot in a rotor disc. The first and second fingers are bent toward each other and engage each other at their ends. Simultaneously, at least a portion of the alignment plate is received in the key slot. During engine operation, the engagement between the alignment plate and the key slot keeps the first and second key pieces aligned. Thus, regardless of the width of either of the two key pieces or the width of the cavity, the fingers remain constantly engaged during engine operation, minimizing the potential for blade liberation.

Abstract: An apparatus for dislodging stuck blades in a turbine engine. The apparatus includes a housing, cam structure, and impact structure. The housing is capable of being temporarily secured to a blade disc structure adjacent to a stuck blade to be dislodged. The cam structure is associated with the housing and is adapted to receive an input torque that rotates the cam structure, the cam structure capable of translating the input torque into an impact force, the impact force including a component in a desired direction. The impact structure is associated with the housing and is capable of receiving the impact force from the cam structure and exerting the impact force on a root area of the stuck blade for dislodging the stuck blade from the blade disc structure non-destructively.

Abstract: A blade closing key system includes a first key piece and a second key piece. The first key piece includes a first finger and an elongated alignment plate. The second key piece includes a second finger and a key slot. The key pieces are installed in a cavity collectively formed by a notch in a blade root and a slot in a rotor disc. The first and second fingers are bent toward each other and engage each other at their ends. Simultaneously, at least a portion of the alignment plate is received in the key slot. During engine operation, the engagement between the alignment plate and the key slot keeps the first and second key pieces aligned. Thus, regardless of the width of either of the two key pieces or the width of the cavity, the fingers remain constantly engaged during engine operation, minimizing the potential for blade liberation.