Certain examples disclose and describe apparatus and methods to provide fast response active clearance control system with piezoelectric actuator. In some examples, an apparatus includes a case surrounding at least part of a turbine engine, the at least part of the turbine engine including at least one of a shroud or a hanger to contain airflow in the at least part of the turbine engine. The apparatus further includes an actuator to control clearance between a blade and the at least one of the shroud or the hanger, the actuator including a multilayer stack of material, and wherein the actuator is outside of the case. The apparatus further includes a rod coupled to the actuator and the at least one of the shroud or the hanger through an opening in the case, the rod to move the at least one of the shroud or the hanger based on the actuator.

Certain examples disclose and describe apparatus and methods to provide fast response active clearance control system with piezoelectric actuator. In some examples, an apparatus includes a case surrounding at least part of a turbine engine, the at least part of the turbine engine including at least one of a shroud or a hanger to contain airflow in the at least part of the turbine engine. The apparatus further includes an actuator to control clearance between a blade and the at least one of the shroud or the hanger, the actuator including a multilayer stack of material, and wherein the actuator is outside of the case. The apparatus further includes a rod coupled to the actuator and the at least one of the shroud or the hanger through an opening in the case, the rod to move the at least one of the shroud or the hanger based on the actuator.

A system for controlling blade tip clearances in a gas turbine engine may comprise an active clearance control system and a controller in operable communication with the active clearance control system. The controller may be configured to identify a cruise condition, reduce a thrust limit of the gas turbine engine to a de-rated maximum climb thrust, determine a first target tip clearance based on the de-rated maximum climb thrust, and send a command signal correlating to the first target tip clearance to the active clearance control system.

A turbomachine rotor blade includes a radially outer end equipped with a heel, the heel being provided with at least one sealing wiper, the or each sealing wiper projecting beyond the heel along a first axis, the first axis being at ±15° with respect to a radial direction, and extending along a second axis, substantially perpendicular to the first axis, between a first upper-surface end and a second lower-surface end, the or each sealing wiper having a first upstream side and a second downstream side as well as a radially outer surface, wherein the or each sealing wiper includes a base attached to the heel and an end piece removably interlocked with the base.

A gas turbine engine actuation system includes a gas turbine engine, an actuation device, an actuator, and a power source. The gas turbine engine includes a compressor section, a combustion section, a turbine section, and a rotating shaft. The actuation device is operable with the compressor section, combustion section, turbine section, or a combination thereof. The actuator is operationally coupled to the actuation device and includes an electric actuator configured to convert electrical current into mechanical power. The power source is configured to supply electrical current to the actuator, alone or in tandem with a hydraulic actuator.

A gas turbine engine actuation system includes a gas turbine engine, an actuation device, an actuator, and a power source. The gas turbine engine includes a compressor section, a combustion section, a turbine section, and a rotating shaft. The actuation device is operable with the compressor section, combustion section, turbine section, or a combination thereof. The actuator is operationally coupled to the actuation device and includes an electric actuator configured to convert electrical current into mechanical power. The power source is configured to supply electrical current to the actuator, alone or in tandem with a hydraulic actuator.

A rotary machine includes: a rotary shaft supported by a bearing provided on a bearing base; and a casing housing the rotary shaft at least in part. The casing includes at least one support leg configured to support the casing on a base plate of a support structure member, and a support leg of the at least one support leg is supported on a support leg base provided on the base plate. The rotary machine further includes a height adjustment mechanism configured to adjust height of the casing, and the height adjustment mechanism includes an inclined surface of a support leg formed on the support leg, an inclined surface of a support leg base formed on the support leg base while facing the inclined surface of the support leg, and an actuator configured to move the support leg and the support leg base relative to each other.

A gas turbine engine is provided. The gas turbine engine includes: a turbomachine; a fan including a plurality of fan blades rotatably driven by the turbomachine; a nacelle surrounding at least in part the plurality of fan blades of the fan; and a clearance control system including a control ring positioned at least partially within the nacelle, coupled to the nacelle, or both for control of a clearance gap between the plurality of fan blades and the nacelle.

A gas turbine engine is provided. The gas turbine engine includes: a turbomachine; a fan including a plurality of fan blades rotatably driven by the turbomachine; a nacelle surrounding at least in part the plurality of fan blades of the fan; and a clearance control system including a control ring positioned at least partially within the nacelle, coupled to the nacelle, or both for control of a clearance gap between the plurality of fan blades and the nacelle.

A gas turbine engine assembly includes adjacent components and a probe assembly. The probe assembly is configured to measure a distance between the probe assembly and blades located radially inward of the adjacent components.