Abstract: A method of health monitoring of a gas turbine engine includes mounting a detection system configured to detect an aeromechanical damping characteristic of a row of airfoils of a gas turbine. An actual aeromechanical damping characteristic of the row of airfoils is measured with the detection system. An output signal is generated indicative of the actual aeromechanical damping characteristic of the row of airfoils. A current flutter characteristic is determined based on the output signal indicative of the actual aeromechanical damping characteristic of the row of airfoils. An airfoil health monitoring system for gas turbine engine and a gas turbine engine are also disclosed.

Abstract: A method of health monitoring of a gas turbine engine includes mounting a detection system configured to detect an aeromechanical damping characteristic of a row of airfoils of a gas turbine. An actual aeromechanical damping characteristic of the row of airfoils is measured with the detection system. An output signal is generated indicative of the actual aeromechanical damping characteristic of the row of airfoils. A current flutter characteristic is determined based on the output signal indicative of the actual aeromechanical damping characteristic of the row of airfoils. An airfoil health monitoring system for gas turbine engine and a gas turbine engine are also disclosed.

Abstract: A shroud for a gas turbine engine includes a leading portion having a leading edge and a first set of circumferentially spaced slots at the leading edge that break up the leading portion into circumferentially spaced segments separated by the first set of slots, and a trailing portion adjacent to the leading portion. The trailing portion has a trailing edge.

Abstract: A shroud suitable for use in combination with an adjacent rotor blade includes a leading portion comprising a first thickness, and a trailing portion adjacent to the leading portion and comprising a second thickness, wherein the second thickness is less than the first thickness so that stiffness in the leading portion is greater than in the trailing portion and radial expansion by thermal growth of the leading portion of the shroud is constrained.

Abstract: A shroud suitable for use in combination with an adjacent rotor blade includes a leading portion comprising a first thickness, and a trailing portion adjacent to the leading portion and comprising a second thickness, wherein the second thickness is less than the first thickness so that stiffness in the leading portion is greater than in the trailing portion and radial expansion by thermal growth of the leading portion of the shroud is constrained.

Abstract: A shroud suitable for use in a gas turbine engine exhibits substantially uniform thermal growth.

Abstract: Disclosed is an airfoil comprising a plurality of ceramic matrix composite (CMC) fabric sheets which are layered to form a single, layered fabric sheet. The layered fabric sheet is formed so as to define a pressure and suction side of the airfoil. The airfoil includes primary fibers which extend radially outwardly from a rotor disk, for example. In this way, the airfoil is suitable for use in a gas turbine engine due to the temperature resistance of CMC and the strength provided by the primary fibers.

Abstract: A shroud suitable for use in a gas turbine engine exhibits substantially uniform thermal growth.

Abstract: A shroud suitable for use in a gas turbine engine exhibits substantially uniform thermal growth.

Abstract: A turbine air sealing and condenser air removal system for use in steam plant equipment is arranged to increase steam plant efficiency, reduce oxygen concentration in condensate being returned to the steam generators, and simplify system arrangement and maintenance. This system incorporates dry running shaft seals at the high and low pressure turbine shaft glands. The turbine shaft glands are exhausted to a vacuum header which is exhausted by vacuum pumps. Air from the condenser is also exhausted to the common vacuum header. Non-rotating air seals on the turbine such as valve stem seals, which must only accommodate linear movement, can incorporate metallic bellows or conventional packings to prevent air leakage into the steam path or steam leakage out into the surrounding environment.

Abstract: A turbine air sealing and condenser air removal system for use in steam plant equipment is arranged to increase steam plant efficiency, reduce oxygen concentration in condensate being returned to the steam generators, and simplify system arrangement and maintenance. This system incorporates dry running shaft seals at the high and low pressure turbine shaft glands. The turbine shaft glands are exhausted to a vacuum header which is exhausted by vacuum pumps. Air from the condenser is also exhausted to the common vacuum header. Non-rotating air seals on the turbine such as valve stem seals, which must only accommodate linear movement, can incorporate metallic bellows or conventional packings to prevent air leakage into the steam path or steam leakage out into the surrounding environment.

Abstract: A turbine air sealing and condenser air removal system for use in steam plant equipment is arranged to increase steam plant efficiency, reduce oxygen concentration in condensate being returned to the steam generators, and simplify system arrangement and maintenance. This system incorporates dry running shaft seals at the high and low pressure turbine shaft glands. The turbine shaft glands are exhausted to a vacuum header which is exhausted by vacuum pumps. Air from the condenser is also exhausted to the common vacuum header. Non-rotating air seals on the turbine such as valve stem seals, which must only accommodate linear movement, can incorporate metallic bellows or conventional packings to prevent air leakage into the steam path or steam leakage out into the surrounding environment.