A shroud assembly including a shroud support and an annular shroud is provided. The shroud assembly includes one or more pins for securing the annular shroud to the shroud support. The pins having a block capable of translating radially to allowing the shroud to expand and contract in the radial direction. A gas turbine engine having a compressor section, a combustion section, a turbine section and a shroud assembly is also provided. The shroud assembly includes one or more pins for securing the continuous shroud to the shroud support. The pins having a block capable of translating radially to allowing the shroud to expand and contract in the radial direction. Methods for assembling a shroud assembly structure in a gas turbine engine are also provided.

Turbine and compressor casing/housing abradable component embodiments for turbine engines, have abradable surfaces with asymmetric forward and aft ridge surface area density. The forward ridges have greater surface area density than the aft ridges to compensate for greater ridge erosion in the forward zone during engine operation and reduce blade tip wear in the aft zone. Some abradable component embodiments increase forward zone ridge surface area density by incorporating wider ridges than those in the aft zone.

Systems and methods for blade health monitoring are provided. According to one embodiment of the disclosure, a system may include a feature extraction module and an anomaly detection module in communication with the extraction module. The feature extraction module may be configured to continuously receive blade passing signal data associated with clearance of a blade and pre-process the blade passing signal data. Blade clearance feature data may be extracted from the blade passing signal data prior to transmission to the anomaly detection module. The anomaly detection module may be configured to normalize the blade clearance feature data received from the extraction module, analyze the blade clearance feature data to detect a shift in the clearance of the blade, and determine an abnormality of the blade based on the shift exceeding a predetermined shift threshold.

Systems and methods for blade health monitoring are provided. According to one embodiment of the disclosure, a system may include a feature extraction module and an anomaly detection module in communication with the extraction module. The feature extraction module may be configured to continuously receive blade passing signal data associated with clearance of a blade and pre-process the blade passing signal data. Blade clearance feature data may be extracted from the blade passing signal data prior to transmission to the anomaly detection module. The anomaly detection module may be configured to normalize the blade clearance feature data received from the extraction module, analyze the blade clearance feature data to detect a shift in the clearance of the blade, and determine an abnormality of the blade based on the shift exceeding a predetermined shift threshold.

A blade for a gas turbine engine includes a fixed length member and a floating blade seal that is movable relative to the floating blade seal to change the length of the blade and vary the gap between the blade and an engine housing component.

A blade for a gas turbine engine includes a fixed length member and a floating blade seal that is movable relative to the floating blade seal to change the length of the blade and vary the gap between the blade and an engine housing component.

The present invention relates to a gas turbine casing arrangement having a gas turbine casing element (10), a guide-vane ring with an outer ring (20), and a coated ring (30), which lies radially opposite a rotor grid (40) adjacent to the guide-vane ring, whereby an intermediate ring (50) by a downstream front face (51) engages behind an upstream stop (61; 61′) fixed in place on the casing element, and by an upstream front face (52) of a radial flange (53) of the intermediate ring engages behind a downstream stop (22) fixed in place on the outer ring, in order to secure the guide-vane ring axially at the gas turbine casing element in the direction of through-flow.

A sealing arrangement includes a stationary component, a first slot is defined between an outer wall and a first inner wall, a second slot is defined between the outer wall and a second inner wall. A rotating component moves in a circumferential direction relative to the stationary component. The rotating component includes a tip rail. A floating seal positioned between the stationary component and the rotating component. The floating seal includes an axial member having a first arm extending into the first slot and a second arm extending into the second slot. The floating seal includes a first radial member and a second radial member that extends from the axial member. A plurality of magnets coupled to the stationary component, the rotating component, and the floating seal. The plurality of magnets is arranged such that the floating seal is contained between the stationary component and the rotating component.

A sealing arrangement includes a stationary component, a first slot is defined between an outer wall and a first inner wall, a second slot is defined between the outer wall and a second inner wall. A rotating component moves in a circumferential direction relative to the stationary component. The rotating component includes a tip rail. A floating seal positioned between the stationary component and the rotating component. The floating seal includes an axial member having a first arm extending into the first slot and a second arm extending into the second slot. The floating seal includes a first radial member and a second radial member that extends from the axial member. A plurality of magnets coupled to the stationary component, the rotating component, and the floating seal. The plurality of magnets is arranged such that the floating seal is contained between the stationary component and the rotating component.

Example apparatus, systems, and articles of manufacture to control deflection mismatch are disclosed herein. Further examples and combinations thereof include: A deflection limiter comprising an inner shroud segment to support a stator structure, the inner shroud segment including a first end face and a first outer upper portion, the first end face positioned radially inward and aft relative to the first outer upper portion, and an outer shroud segment to support the inner shroud segment, the outer shroud segment including a second end face and a second outer upper portion, the second end face positioned aft relative to the first end face and the second outer upper portion positioned aft relative to the first outer upper portion of the inner shroud segment, the second end face coupled to the first end face of the inner shroud segment and the second outer upper portion coupled to the first outer upper portion.