Abstract: A first actuator moves a compressor rotor and compressor blades along a rotational axis of the compressor rotor. A turbine rotor includes a plurality of turbine blades each extending radially outwardly from the turbine rotor to an outer tip. A turbine housing surrounds each of the turbine blade tips. The turbine housing has an inner surface, and a turbine tip clearance is defined between each of the turbine blade tips and the inner surface of the turbine housing. A second actuator moves the turbine rotor and the turbine blades along a rotational axis of the turbine rotor. A control controls the first actuator of the compressor rotor, and the second actuator of the turbine rotor to control the compressor tip clearance and the turbine tip clearance.

Abstract: A system and method for coupling cases associated with an engine of an aircraft. A first case includes a first plurality of threads. A second case includes a second plurality of threads. A coupler includes a third plurality of threads and a fourth plurality of threads. An interface is configured to align the first case and the second case before the first plurality of threads engage the third plurality of threads or the second plurality of threads engage the fourth plurality of threads.

Abstract: A borescope plug includes a threaded section that extends from a head section along an axis, the threaded section including a central passage along said axis. A spindle is located within the central passage. A multiple of detents are positioned in response to an axial position of the spindle along the axis.

Abstract: A first case includes a first plurality of threads, a second case includes a second plurality of threads, an interface provides at least one of anti-rotation or alignment with respect to the first case and the second case, and a nut includes a third plurality of threads configured to engage with the first plurality of threads and a fourth plurality of threads configured to engage with the second plurality of threads.

Abstract: A system and method for coupling cases associated with an engine of an aircraft. A first case includes a first plurality of threads. A second case includes a second plurality of threads. A coupler includes a third plurality of threads and a fourth plurality of threads. An interface is configured to align the first case and the second case before the first plurality of threads engage the third plurality of threads or the second plurality of threads engage the fourth plurality of threads.

Abstract: A system and method for coupling cases associated with an engine of an aircraft. A first case includes a first plurality of threads. A second case includes a second plurality of threads. A coupler includes a third plurality of threads and a fourth plurality of threads. An interface is configured to align the first case and the second case before the first plurality of threads engage the third plurality of threads or the second plurality of threads engage the fourth plurality of threads.

Abstract: A borescope plug includes a threaded section that extends from a head section along an axis, the threaded section including a central passage along said axis. A spindle is located within the central passage. A multiple of detents are positioned in response to an axial position of the spindle along the axis.

Abstract: The present disclosure relates to sealing systems for gas turbine engines. In one embodiment, a seal support structure for a gas turbine engine includes a seal support configured to retain a circumferential seal and an engine support configured for mounting the seal support structure to a gas turbine engine mount. The engine support includes at least one channel configured to provide radial movement of the seal support structure and circumferential retention of the seal support. Another embodiment is directed to a sealing system including a circumferential seal and seal support structure configured to provide radial movement.

Abstract: A borescope plug includes a threaded section that extends from a head section along an axis, the threaded section including a central passage along said axis. A spindle is located within the central passage. A multiple of detents are positioned in response to an axial position of the spindle along the axis.

Abstract: What is described is a tree seal for use on a rotating element. The tree seal includes a trunk configured to be coupled to the rotating element. The tree seal also includes a first branch coupled to the trunk and having a first edge configured to form a first mini seal with a housing. The tree seal also includes a second branch coupled to the trunk and having a second edge configured to form a second mini seal with the housing.

Abstract: A gas turbine engine section has a housing and a plurality of panels attached to the housing. The panels face toward a flow path of hot products of combustion. The panels include a central web and extending legs. A bend between the central web and the extending legs is formed at a radius. A gas turbine engine is also disclosed.

Abstract: Aspects of the disclosure are directed to coupling cases associated with an engine of an aircraft. A first case includes a first plurality of threads. A second case includes a second plurality of threads. A coupler includes a third plurality of threads and a fourth plurality of threads. An interface is configured to align the first case and the second case before the first plurality of threads engage the third plurality of threads or the second plurality of threads engage the fourth plurality of threads.

Abstract: Aspects of the disclosure are directed to a first case including a first plurality of threads, a second ease including a second plurality of threads, an interface configured to provide for at least one of anti-rotation or alignment with respect to the first case and the second ease, and a nut including a third plurality of threads configured to engage with the first plurality of threads and a fourth plurality of threads configured to engage with the second plurality of threads.

Abstract: A first actuator moves a compressor rotor and compressor blades along a rotational axis of the compressor rotor. A turbine rotor includes a plurality of turbine blades each extending radially outwardly from the turbine rotor to an outer tip. A turbine housing surrounds each of the turbine blade tips. The turbine housing has an inner surface, and a turbine tip clearance is defined between each of the turbine blade tips and the inner surface of the turbine housing. A second actuator moves the turbine rotor and the turbine blades along a rotational axis of the turbine rotor. A control controls the first actuator of the compressor rotor, and the second actuator of the turbine rotor to control the compressor tip clearance and the turbine tip clearance.

Abstract: What is described is a tree seal for use on a rotating element. The tree seal includes a trunk configured to be coupled to the rotating element. The tree seal also includes a first branch coupled to the trunk and having a first edge configured to form a first mini seal with a housing. The tree seal also includes a second branch coupled to the trunk and having a second edge configured to form a second mini seal with the housing.

Abstract: A borescope plug includes a threaded section that extends from a head section along an axis, the threaded section including a central passage along said axis. A spindle is located within the central passage. A multiple of detents are positioned in response to an axial position of the spindle along the axis.

Abstract: The present disclosure relates to sealing systems for gas turbine engines. In one embodiment, a seal support structure for a gas turbine engine includes a seal support configured to retain a circumferential seal and an engine support configured for mounting the seal support structure to a gas turbine engine mount. The engine support includes at least one channel configured to provide radial movement of the seal support structure and circumferential retention of the seal support. Another embodiment is directed to a sealing system including a circumferential seal and seal support structure configured to provide radial movement.

Abstract: A seal assembly for a fan duct metering valve disposed within a casing of a gas turbine engine includes a tab for extending through an opening in the casing and attaching to the valve, a carrier for extending into the opening and engaging the valve such that fluid does not leak between the valve and the carrier.

Abstract: A flowpath assembly for a gas turbine engine includes a plurality of flowpath insert ducts arranged in a cascade configuration. Each flowpath duct includes a radially inward wall, a radially outward wall, a first side wall, and a second side wall. A flowpath volume is defined between the inward, outward, first side and second side walls. The first side wall of a given one of the plurality of flowpath insert ducts is positioned adjacent to the second sidewall of an adjacent one of the plurality of flowpath insert ducts in the cascade configuration.

Abstract: A flowpath assembly for a gas turbine engine includes a plurality of flowpath insert ducts arranged in a cascade configuration. Each flowpath duct includes a radially inward wall, a radially outward wall, a first side wall, and a second side wall. A flowpath volume is defined between the inward, outward, first side and second side walls. The first side wall of a given one of the plurality of flowpath insert ducts is positioned adjacent to the second sidewall of an adjacent one of the plurality of flowpath insert ducts in the cascade configuration.