Abstract: A heated inlet guide vane is disclosed. The disclosed guide vane may include a body having an inlet cavity disposed alongside of an outlet cavity wherein the outlet cavity is disposed alongside the leading edge of the vane. The inlet cavity is in communication with a source of heated air. The inlet cavity is in communication with the outlet cavity by way of a plurality of impingement holes spaced along the inner wall disposed between the two cavities. Bleed holes are spaced along the length of the outlet cavity. Fresh, heated air enters the outlet cavity along the entire length of the outlet cavity and quickly exits the outlet cavity with minimal cooling so that a uniform d-icing capability is provided along the entire leading edge of the inlet guide vane.

Abstract: A manifold for a gas turbine engine includes oppositely facing first and second walls that extend from an annular wall. An undulating wall oppositely faces the annular wall and couples the first wall to the second wall. The walls collectively form a plurality of first chambers in fluid communication with a plurality of second chambers so that each of the second chambers intersperse adjacent first chambers. Each first chamber has a first volume that is greater that a second volume of each second chamber.

Abstract: A gas turbine engine has a plurality of compressor rotors, as well as a plurality of turbine rotors. A tie shaft of the engine is constrained to rotate with the compressor and turbine rotors during normal operating conditions. Further, an upstream hub is in threaded engagement with the tie shaft. The threads of the upstream hub are handed in a first manner when viewed from an upstream location. A downstream abutment member is positioned downstream of the turbine rotors and is also in threaded engagement with the tie shaft. Threads of the downstream abutment member are handed in the first manner when viewed from a downstream location. Accordingly, the compressor and turbine sections of the engine are reliably held together, and the tie shaft is substantially prevented from unwinding.

Abstract: A heated inlet guide vane is disclosed. The disclosed guide vane may include a body having an inlet cavity disposed alongside of an outlet cavity wherein the outlet cavity is disposed alongside the leading edge of the vane. The inlet cavity is in communication with a source of heated air. The inlet cavity is in communication with the outlet cavity by way of a plurality of impingement holes spaced along the inner wall disposed between the two cavities. Bleed holes are spaced along the length of the outlet cavity. Fresh, heated air enters the outlet cavity along the entire length of the outlet cavity and quickly exits the outlet cavity with minimal cooling so that a uniform d-icing capability is provided along the entire leading edge of the inlet guide vane.

Abstract: A manifold for a gas turbine engine includes oppositely facing first and second walls that extend from an annular wall. An undulating wall oppositely faces the annular wall and couples the first wall to the second wall. The walls collectively form a plurality of first chambers in fluid communication with a plurality of second chambers so that each of the second chambers intersperse adjacent first chambers. Each first chamber has a first volume that is greater that a second volume of each second chamber.

Abstract: A turbomachine includes a tie shaft extending along an axis. Multiple rotors are mounted on the tie shaft. First and second clamping members are secured to the tie shaft and exert a clamping load between the rotors and clamping members at multiple interfaces. The clamping load at one of the interfaces includes a radial clamping load of greater than 5% of a total design clamping load at the one interface. In one example, one of the clamping members is provided by a hub including a first leg extending between first and second opposing ends. The first end provides a flange configured to be supported by the tie shaft. The second end includes first and second hub surfaces respectively extending in radial and axial directions. The first leg is inclined between 15° and 75° relative to the axial direction.

Abstract: An anti-vortex assembly for a gas turbine engine includes a support ring including a seat surrounding an opening and a bleed tube including a base with a bearing face sealing against the seat. A retaining ring is mounted within the support ring and engages the base of the bleed air tube to hold the bleed tube within the support ring.

Abstract: A gas turbine engine assembly includes a rotor shaft having a threaded portion, a rotor stack support positioned radially outward from the rotor shaft, and a locking nut. The locking nut includes a body portion, a threaded portion located on a radially inner surface of the body portion, and a lug portion extending from the body portion. The rotor stack support radially rests upon the body portion of the locking nut, and the rotor stack support axially rests against the lug portion of the locking nut. The threaded portion of the locking nut and the threaded portion of the rotor shaft are engaged together.

Abstract: A turbomachine includes a tie shaft extending along an axis. Multiple rotors are mounted on the tie shaft. First and second clamping members are secured to the tie shaft and exert a clamping load between the rotors and clamping members at multiple interfaces. The clamping load at one of the interfaces includes a radial clamping load of greater than 5% of a total design clamping load at the one interface. In one example, one of the clamping members is provided by a hub including a first leg extending between first and second opposing ends. The first end provides a flange configured to be supported by the tie shaft. The second end includes first and second hub surfaces respectively extending in radial and axial directions. The first leg is inclined between 15° and 75° relative to the axial direction.

Abstract: A gas turbine engine has a compressor section carrying a plurality of compressor rotors and a turbine section carrying a plurality of turbine rotors. The compressor rotors and the turbine rotors are constrained to rotate with the tie shaft. An upstream hub provides an upstream abutment face for the compressor rotors. A downstream hub bounds the downstream end of the compressor rotor to bias the compressor rotors against the upstream hub using an abutment member. The downstream hub has a rearwardly extending arm which provides a stop for the turbine rotors. A second abutment member is tightened on the tie shaft to force the turbine rotors against the downstream hub to hold together the turbine rotors.

Abstract: A gas turbine engine has a plurality of compressor rotors, as well as a plurality of turbine rotors. A tie shaft of the engine is constrained to rotate with the compressor and turbine rotors during normal operating conditions. Further, an upstream hub is in threaded engagement with the tie shaft. The threads of the upstream hub are handed in a first manner when viewed from an upstream location. A downstream abutment member is positioned downstream of the turbine rotors and is also in threaded engagement with the tie shaft. Threads of the downstream abutment member are handed in the first manner when viewed from a downstream location. Accordingly, the compressor and turbine sections of the engine are reliably held together, and the tie shaft is substantially prevented from unwinding.

Abstract: A compressor section to be mounted in a gas turbine engine has a plurality of axial compressor rotors arranged from an upstream location toward a downstream location. A tie shaft applies an axial force at one end of the compressor section and biases the compressor rotors against a hub at the opposite end. The downstream compressor is an axial compressor rotor. A gas turbine engine incorporating this structure is also claimed.

Abstract: A gas turbine engine has a compressor section carrying a plurality of compressor rotors and a turbine section carrying a plurality of turbine rotors. The compressor rotors and the turbine rotors are constrained to rotate with the tie shaft. An upstream hub provides an upstream abutment face for the compressor rotors. A downstream hub bounds the downstream end of the compressor rotor to bias the compressor rotors against the upstream hub using an abutment member. The downstream hub has a rearwardly extending arm which provides a stop for the turbine rotors. A second abutment member is tightened on the tie shaft to force the turbine rotors against the downstream hub to hold together the turbine rotors.

Abstract: A gas turbine engine assembly includes a rotor shaft having a threaded portion, a rotor stack support positioned radially outward from the rotor shaft, and a locking nut. The locking nut includes a body portion, a threaded portion located on a radially inner surface of the body portion, and a lug portion extending from the body portion. The rotor stack support radially rests upon the body portion of the locking nut, and the rotor stack support axially rests against the lug portion of the locking nut. The threaded portion of the locking nut and the threaded portion of the rotor shaft are engaged together.