Abstract: A rotor blade assembly for a turbine engine, including an airfoil blade including an inner diameter end and an outer diameter end, a lower blade carrier coupled to the inner diameter end of the airfoil blade and rigidly coupled to a disk via a pin, an upper blade carrier coupled to the outer diameter end of the airfoil blade, and an outer drum coupled to the upper blade carrier via a radial joint. The radial joint supports radial motion of the upper blade carrier relative to an axis extending through a center of the rotor blade assembly.

Abstract: A rotor blade assembly for a turbine engine, including an airfoil blade including an inner diameter end and an outer diameter end, a lower blade carrier coupled to the inner diameter end of the airfoil blade and rigidly coupled to a disk via a pin, an upper blade carrier coupled to the outer diameter end of the airfoil blade, and an outer drum coupled to the upper blade carrier via a radial joint. The radial joint supports radial motion of the upper blade carrier relative to an axis extending through a center of the rotor blade assembly.

Abstract: Structures, such as compressor casings, for reducing a thermal gradient are provided. For example, a compressor case is split such that it includes first and second case segments. The first case segment extends over a first portion of the compressor case circumference and comprises a first inner structure, a first outer structure, and a first porous structure integrally formed as a monolithic component. The first porous structure is defined between the first inner structure and the first outer structure. The second case segment extends over a second portion of the compressor case circumference and comprises a second inner structure, a second outer structure, and a second porous structure integrally formed as a monolithic component. The second porous structure is defined between the second inner structure and the second outer structure. Methods of cooling structures such as compressor casings also are provided.

Abstract: Methods, apparatus, systems and articles of manufacture for compact compressors are disclosed including a gas turbine engine defining an axial direction and a radial direction, the gas turbine engine including an axial flow compressor and a radial flow compressor, wherein the axial flow compressor is located axially forward of the radial flow compressor, a blade assembly including a splitter shroud to divide incoming air into axial air flow for the axial flow compressor and radial air flow for the radial flow compressor, the blade assembly rotating relative to the axial flow compressor and counter-rotating relative to the radial flow compressor, and wherein the blade assembly is located axially aft of the radial flow compressor.

Abstract: Structures, such as compressor casings, for reducing a thermal gradient are provided. For example, a compressor case is split such that it includes first and second case segments. The first case segment extends over a first portion of the compressor case circumference and comprises a first inner structure, a first outer structure, and a first porous structure integrally formed as a monolithic component. The first porous structure is defined between the first inner structure and the first outer structure. The second case segment extends over a second portion of the compressor case circumference and comprises a second inner structure, a second outer structure, and a second porous structure integrally formed as a monolithic component. The second porous structure is defined between the second inner structure and the second outer structure. Methods of cooling structures such as compressor casings also are provided.

Abstract: Methods, apparatus, systems and articles of manufacture for compact compressors are disclosed including a gas turbine engine defining an axial direction and a radial direction, the gas turbine engine including an axial flow compressor and a radial flow compressor, wherein the axial flow compressor is located axially forward of the radial flow compressor, a blade assembly including a splitter shroud to divide incoming air into axial air flow for the axial flow compressor and radial air flow for the radial flow compressor, the blade assembly rotating relative to the axial flow compressor and counter-rotating relative to the radial flow compressor, and wherein the blade assembly is located axially aft of the radial flow compressor.

Abstract: A vibration isolation system for a gas turbine engine. The vibration isolation system includes a first fixed structure and a second fixed structure separate from the first fixed structure. The vibration isolation system further includes a connector coupling the first fixed structure to the second fixed structure. Additionally, the vibration isolation system includes an isolator, including a shape memory alloy material, associated with the connector. The isolator is arranged between the first fixed structure and the second fixed structure such that the isolator reduces vibrations transferred between the first fixed structure and the second fixed structure.

Abstract: A tube coupling assembly is disclosed, which comprises a first connector for connecting to a tube; a second connector for jointing with the first connector; a first member is adapted to mount on the first connector and operably affixable to the second connector; and a second member is adapted to mount on the second connector, and is capable of being engaged with the first member to prevent separation between the first connector and the second connector.

Abstract: A turbine assembly including a first rotor assembly with a rotatable outer drum from which one or more stages of a plurality of outer drum airfoils is extended radially inward is provided. An outer casing surrounds the outer drum of the first rotor assembly. A seal assembly is coupled to the outer casing and positioned radially outward from an upstream-most stage of the plurality of outer drum airfoils. The seal assembly is positioned in axial alignment with the upstream-most stage of the plurality of outer drum airfoils. The seal assembly separates a first plenum from a second plenum. The second plenum is formed axially aft of the first plenum and is formed by the seal assembly, the outer casing, and the outer drum of the first rotor assembly. The first plenum is positioned radially outward from the upstream-most stage of the plurality of outer drum airfoils.

Abstract: The present disclosure is directed generally to firewall seals for sealing pass-through members extending through a firewall, such as a firewall of a turbine engine. In one example aspect, the firewall seal includes quick-connect features that facilitate more efficient assembly and disassembly of the firewall seal to and from the pass-through member. Particularly, the firewall seal may define a slit extending through at least a portion of the seal that allows for the pass-through member to be slid through the slit and positioned in place. A retainer formed of an elastomeric material may include a metal spring plate that springs the seal back into place after the pass-through member is positioned within the seal. Moreover, a spherical bearing of the firewall seal may include features for receiving a static or dynamic pass-through member therethrough and for allowing the pass-through member to translate and rotate.

Abstract: A vibration isolation system for a gas turbine engine. The vibration isolation system includes a first fixed structure and a second fixed structure separate from the first fixed structure. The vibration isolation system further includes a connector coupling the first fixed structure to the second fixed structure. Additionally, the vibration isolation system includes an isolator, including a shape memory alloy material, associated with the connector. The isolator is arranged between the first fixed structure and the second fixed structure such that the isolator reduces vibrations transferred between the first fixed structure and the second fixed structure.

Abstract: The present disclosure is directed generally to firewall seals for sealing pass-through members extending through a firewall, such as a firewall of a turbine engine. In one example aspect, the firewall seal includes quick-connect features that facilitate more efficient assembly and disassembly of the firewall seal to and from the pass-through member. Particularly, the firewall seal may define a slit extending through at least a portion of the seal that allows for the pass-through member to be slid through the slit and positioned in place. A retainer formed of an elastomeric material may include a metal spring plate that springs the seal back into place after the pass-through member is positioned within the seal. Moreover, a spherical bearing of the firewall seal may include features for receiving a static or dynamic pass-through member therethrough and for allowing the pass-through member to translate and rotate.

Abstract: A manifold for use in a clearance control system is provided. The clearance control system includes a housing including a plurality of walls that at least partially define an interior of the housing, and a nozzle portion integrally formed with the housing. The nozzle portion extends between adjacent walls of the plurality of walls and including at least one nozzle projection having a plurality of impingement openings defined therethrough. The at least one nozzle projection extends from the adjacent walls in an outward direction relative to the interior of the housing.

Abstract: Arcuate panel includes at least one axially extending panel header with arcuate outer and inner portions. Inner portion includes open portions of axially spaced apart arcuate cooling air spray rails attached to header and in fluid communication with plenum within header. Plurality of axially extending hollow fingers extend axially away from one of the spray rails and impingement spray holes in the spray rails and the fingers. Arcuate overhang may extend axially aftwardly from one of the spray rails and fingers may depend from overhang. An outer casing including axially spaced apart forward and aft casing flanges attached to or integral and monolithic with outer casing may be circumscribed by a hoop of the arcuate panels. The fingers may extend away from one of the spray rails and between nuts screwed on bolts disposed through one of the forward and aft casing flanges.

Abstract: A tube coupling assembly is disclosed, which comprises a first connector for connecting to a tube; a second connector for jointing with the first connector; a first member is adapted to mount on the first connector and operably affixable to the second connector; and a second member is adapted to mount on the second connector, and is capable of being engaged with the first member to prevent separation between the first connector and the second connector.

Abstract: A manifold for use in a clearance control system is provided. The clearance control system includes a housing including a plurality of walls that at least partially define an interior of the housing, and a nozzle portion integrally formed with the housing. The nozzle portion extends between adjacent walls of the plurality of walls and including at least one nozzle projection having a plurality of impingement openings defined therethrough. The at least one nozzle projection extends from the adjacent walls in an outward direction relative to the interior of the housing.