Abstract: An axial location of a time of arrival probe may be determined by attaching a wedge comprising a distal surface to a blade. A first edge of the distal surface and a second edge of the distal surface may form an angle. The axial location of the probe may be determined based on the angle and a distance extending from the first edge of the wedge to the blade.

Abstract: A performance measurement system of an inlet of a gas turbine engine includes a probe strut configured for installation to a case strut of an inlet case of a gas turbine engine. The probe strut includes one or more probes extending therefrom configured to measure one or more characteristics of an airflow past the one or more probes, a first attachment point configured to secure the probe strut to a hub portion of the inlet case, and a second attachment point configured to secure the probe strut to an outer case portion of the inlet case. A data acquisition module is located at a central longitudinal axis of the inlet and is operably connected to the probe to collect sensed data therefrom. The probe strut and the data acquisition module are configured to be installed, removed, and/or relocated without removal of the inlet case from the gas turbine engine.

Abstract: A deflection measurement assembly according to an example of the present disclosure includes, among other things, a nacelle arranged about an axis to define a flow path, a cable assembly arranged at least partially about the axis, and a transducer coupled to the cable assembly.

Abstract: A performance measurement system of an inlet of a gas turbine engine includes a probe strut configured for installation to a case strut of an inlet case of a gas turbine engine. The probe strut includes one or more probes extending therefrom configured to measure one or more characteristics of an airflow past the one or more probes, a first attachment point configured to secure the probe strut to a hub portion of the inlet case, and a second attachment point configured to secure the probe strut to an outer case portion of the inlet case. A data acquisition module is located at a central longitudinal axis of the inlet and is operably connected to the probe to collect sensed data therefrom. The probe strut and the data acquisition module are configured to be installed, removed, and/or relocated without removal of the inlet case from the gas turbine engine.

Abstract: An axial location of a time of arrival probe may be determined by attaching a wedge comprising a distal surface to a blade. A first edge of the distal surface and a second edge of the distal surface may form an angle. The axial location of the probe may be determined based on the angle and a distance extending from the first edge of the wedge to the blade.

Abstract: A pressure probe includes a non-deflecting airfoil, a sensing feature, and an interior passage. The non-deflecting airfoil is made of a metal and configured for use in a gas turbine engine. The airfoil extends from a base to a tapered portion, and then to a linear portion, along a primary axis. The sensing feature is formed monolithically with the airfoil, as by additive manufacturing. The interior passage is operatively connected to the sensing feature and passes through both the airfoil and the base.

Abstract: A modular egress seal assembly includes an annular plate with an axially extending aperture. A base plate is mountable to the annular plate. The base plate includes an aperture extending along the axis when said base plate is mounted to the annular plate thereby forming an axial passageway and a cover plate mountable to said annular plate.

Abstract: A deflection measurement assembly according to an example of the present disclosure includes, among other things, a nacelle arranged about an axis to define a flow path, a cable assembly arranged at least partially about the axis, and a transducer coupled to the cable assembly.

Abstract: A pressure probe includes a non-deflecting airfoil, a sensing feature, and an interior passage. The non-deflecting airfoil is made of a metal and configured for use in a gas turbine engine. The airfoil extends from a base to a tapered portion, and thence to a linear portion, along a primary axis. The sensing feature is formed monolithically with the airfoil, as by additive manufacturing. The interior passage is operatively connected to the sensing feature and passes through both the airfoil and the base.

Abstract: An example turbomachine probe assembly includes a probe body extending along a probe axis from a first sensor end to an opposing second end. An eccentric retention feature is configured to engage the probe body into contact with wall having an aperture that receives the probe body. The eccentric retention feature limits movement of the probe body along the probe axis relative to the wall.

Abstract: A modular egress seal assembly includes an annular plate with an axially extending aperture. A base plate is mountable to the annular plate. The base plate includes an aperture extending along the axis when said base plate is mounted to the annular plate thereby forming an axial passageway and a cover plate mountable to said annular plate.

Abstract: An example turbomachine probe assembly includes a probe body extending along a probe axis from a first sensor end to an opposing second end. An eccentric retention feature is configured to engage the probe body into contact with wall having an aperture that receives the probe body. The eccentric retention feature limits movement of the probe body along the probe axis relative to the wall.

Abstract: A diaper dispenser apparatus includes a housing having an interior region. The housing includes a front panel formed to include an aperture therein. The apparatus also includes a spring loaded platform located in an interior region of the housing. The platform is configured to support a stack of diapers and to locate a top diaper on the stack in alignment with the aperture in the front panel of the housing to permit removal of the top diaper through the aperture.