Abstract: A combustor assembly for a gas turbine engine including an outer casing, the gas turbine engine defining an axial direction, the combustor assembly includes a liner at least partially defining a combustion chamber extending between an aft end and a forward end generally along the axial direction within the outer casing, the liner including an inner surface facing the combustion chamber and an outer surface facing away from the combustion chamber, and a damper assembly extending between the outer casing and the outer surface of the liner, the damper assembly including a selectively separable support and a damper spring, the damper spring being disposed between the support and the liner.

Abstract: A combustor assembly for a gas turbine engine including an outer casing, the gas turbine engine defining an axial direction, the combustor assembly includes a liner at least partially defining a combustion chamber extending between an aft end and a forward end generally along the axial direction within the outer casing, the liner including an inner surface facing the combustion chamber and an outer surface facing away from the combustion chamber, and a damper assembly extending between the outer casing and the outer surface of the liner, the damper assembly including a selectively separable support and a damper spring, the damper spring being disposed between the support and the liner.

Abstract: A combustor assembly for a gas turbine engine includes an outer liner that at least partially defines a combustion chamber. The outer liner extends between an aft end and a forward end generally along an axial direction within an outer casing of the gas turbine engine. The outer liner includes an inner surface facing the combustion chamber and an outer surface facing away from the combustion chamber. The combustor assembly includes a radial damper assembly disposed against the outer liner at a plurality of circumferential points.

Abstract: In one embodiment, a method includes receiving code including multiple snippets programmed for manipulating objects in an extended reality environment; using a machine-learning model to learn to identify multiple coding patterns from the multiple snippets programmed for manipulating objects; extracting, based on the multiple coding patterns, object terms and relationships between the object terms used in the multiple snippets; generating an ontology for a natural language model based on the object terms and the relationships, wherein the ontology is configured to be used by the natural language model to parse speech into intents and slots.

Abstract: A gas turbine engine is provided having a combustion section with a liner extending between a forward end and an aft end. A structural member is positioned in or around at least a portion of the combustion section. Additionally, a piston ring holder is provided attached to the structural member at a first end and positioned proximate to the aft end of the liner at a second end. The piston ring holder is a bimetallic member including a first portion formed of a first material and a second portion formed of a second material. A coefficient of thermal expansion of the first material is different than a coefficient of thermal expansion of the second material.

Abstract: Systems and methods are provided for determining the frequency of a cardiovascular pulse based on a first physiological signal that is continuously available and a second physiological signal that is less available and that is more accurate or otherwise improved relative to the first signal with respect to pulse rate estimation. When the second signal is available it controls the determination of the pulse rate. When the second signal is unavailable, the first signal is used to determine the pulse rate. This can include using the first signal to estimate the pulse rate until the second signal is available, at which point the pulse rate is estimated based on the second physiological signal. Alternatively, the first signal could be used to determine a number of candidate pulse rates, and the second signal could be used to select a pulse rate from the set of candidate pulse rates.

Abstract: A gas turbine engine is provided having a combustion section with a liner extending between a forward end and an aft end. A structural member is positioned in or around at least a portion of the combustion section. Additionally, a piston ring holder is provided attached to the structural member at a first end and positioned proximate to the aft end of the liner at a second end. The piston ring holder is a bimetallic member including a first portion formed of a first material and a second portion formed of a second material. A coefficient of thermal expansion of the first material is different than a coefficient of thermal expansion of the second material.

Abstract: A gas turbine engine is provided having a combustion section with a liner extending between a forward end and an aft end. A structural member is positioned in or around at least a portion of the combustion section. Additionally, a piston ring holder is provided attached to the structural member at a first end and positioned proximate to the aft end of the liner at a second end. The piston ring holder is a bimetallic member including a first portion formed of a first material and a second portion formed of a second material. A coefficient of thermal expansion of the first material is different than a coefficient of thermal expansion of the second material.

Abstract: A combustor assembly for a gas turbine engine includes an outer liner that at least partially defines a combustion chamber. The outer liner extends between an aft end and a forward end generally along an axial direction within an outer casing of the gas turbine engine. The outer liner includes an inner surface facing the combustion chamber and an outer surface facing away from the combustion chamber. The combustor assembly includes a radial damper assembly disposed against the outer liner at a plurality of circumferential points.

Abstract: A gas turbine engine and combustor assembly is generally provided. The gas turbine engine may include an outer casing while the combustor assembly may include a liner and a damper assembly. The liner may at least partially define a combustion chamber extending between an aft end and a forward end generally along an axial direction within the outer casing. The liner may include an inner surface facing the combustion chamber and an outer surface facing away from the combustion chamber. The damper assembly may extend between the outer casing and the outer surface of the liner. The damper assembly may include a selectively separable support and damper spring. The damper spring may be disposed between the support and the liner.

Abstract: Systems and methods are provided for determining the frequency of a cardiovascular pulse based on a first physiological signal that is continuously available and a second physiological signal that is less available and that is more accurate or otherwise improved relative to the first signal with respect to pulse rate estimation. When the second signal is available it controls the determination of the pulse rate. When the second signal is unavailable, the first signal is used to determine the pulse rate. This can include using the first signal to estimate the pulse rate until the second signal is available, at which point the pulse rate is estimated based on the second physiological signal. Alternatively, the first signal could be used to determine a number of candidate pulse rates, and the second signal could be used to select a pulse rate from the set of candidate pulse rates.

Abstract: Systems and methods are provided for determining the frequency of a cardiovascular pulse based on a first physiological signal that is continuously available and a second physiological signal that is less available and that is more accurate or otherwise improved relative to the first signal with respect to pulse rate estimation. When the second signal is available it controls the determination of the pulse rate. When the second signal is unavailable, the first signal is used to determine the pulse rate. This can include using the first signal to estimate the pulse rate until the second signal is available, at which point the pulse rate is estimated based on the second physiological signal. Alternatively, the first signal could be used to determine a number of candidate pulse rates, and the second signal could be used to select a pulse rate from the set of candidate pulse rates.

Abstract: Components and methods for forming components are provided. For example, a method for forming a component includes laying up a plurality of plies to form a component preform that defines an axis of symmetry and a circumferential direction. Laying up the plurality of plies includes overlapping ends of the plurality of plies to define overlap regions and offsetting the overlap regions along the circumferential direction such that any radial line drawn from the axis of symmetry through the plies passes through only one overlap region. In another embodiment, a component includes a body that is symmetric about an axis of symmetry and that defines a circumferential direction and a radial direction. The body is formed from a plurality of plies and has a substantially uniform thickness. Ends of the plurality of plies are overlapped to define a plurality of overlap regions, which are offset along the circumferential direction.

Abstract: A combustor assembly for a gas turbine engine is provided. The combustor assembly includes a liner at least partially defining a combustion chamber and extending between an aft end a forward end generally along an axial direction. The combustor assembly also includes an annular dome including an enclosed surface defining a slot for receipt of the forward end of the liner. A cap is positioned at the forward end of the liner and at least partially positioned within the slot defined by the enclosed surface of the annular dome. The cap includes a surface configured to contact at least one of the enclosed surface of the annular dome and the forward end of the liner. Such a configuration may form a substantially airtight seal between the forward end of the liner and the annular dome despite a relative thermal expansion between the components.

Abstract: Systems and methods are provided for determining the frequency of a cardiovascular pulse based on a photoplethysmographic measurement of blood in a portion of subsurface vasculature. A plurality of samples of the photoplethysmographic signal are obtained and a frequency spectrum determined based on a first set of the plurality of samples. A frequency is determined based on a maximum frequency component of the frequency spectrum. Further, a confidence level of the determined frequency of the maximum frequency component is determined based on the magnitude of the maximum frequency component and the overall energy in the frequency spectrum. A pulse rate is then determined by updating a predicted pulse rate of a second, earlier set of the plurality of samples based on the frequency of the maximum frequency component and the determined confidence level.

Abstract: A combustor assembly for a gas turbine engine is provided. The combustor assembly includes a liner at least partially defining a combustion chamber and extending between an aft end a forward end generally along an axial direction. The combustor assembly also includes an annular dome including an enclosed surface defining a slot for receipt of the forward end of the liner. A cap is positioned at the forward end of the liner and at least partially positioned within the slot defined by the enclosed surface of the annular dome. The cap includes a surface configured to contact at least one of the enclosed surface of the annular dome and the forward end of the liner. Such a configuration may form a substantially airtight seal between the forward end of the liner and the annular dome despite a relative thermal expansion between the components.

Abstract: A combustor assembly for a gas turbine engine is provided. The combustor assembly generally includes an annular dome and a liner. The liner at least partially defines a combustion chamber and includes the forward end received within a slot defined by the annular dome. A mounting assembly attaches the forward end of the liner to the annular dome. The mounting assembly includes a pin extending through the slot and the forward end of the annular dome. The mounting assembly also includes a grommet positioned in an opening in the forward end of the liner. The grommet is also positioned around the pin to protect the liner during operation of the gas turbine engine.

Abstract: Components and methods for forming components are provided. For example, a method for forming a component includes laying up a plurality of plies to form a component preform that defines an axis of symmetry and a circumferential direction. Laying up the plurality of plies includes overlapping ends of the plurality of plies to define overlap regions and offsetting the overlap regions along the circumferential direction such that any radial line drawn from the axis of symmetry through the plies passes through only one overlap region. In another embodiment, a component includes a body that is symmetric about an axis of symmetry and that defines a circumferential direction and a radial direction. The body is formed from a plurality of plies and has a substantially uniform thickness. Ends of the plurality of plies are overlapped to define a plurality of overlap regions, which are offset along the circumferential direction.

Abstract: A gas turbine engine and combustor assembly is generally provided. The gas turbine engine may include an outer casing while the combustor assembly may include a liner and a damper assembly. The liner may at least partially define a combustion chamber extending between an aft end and a forward end generally along an axial direction within the outer casing. The liner may include an inner surface facing the combustion chamber and an outer surface facing away from the combustion chamber. The damper assembly may extend between the outer casing and the outer surface of the liner. The damper assembly may include a selectively separable support and damper spring. The damper spring may be disposed between the support and the liner.

Abstract: Systems and methods are provided for determining a pulse rate based on a photoplethysmographic measurement of blood in a portion of subsurface vasculature. A plurality of samples of the photoplethysmographic signal are obtained and a plurality of digital phase-locked loops are operated to generate respective oscillating signals based on the plurality of samples. Respective correlations between the plurality of samples and each of the generated oscillating signals are determined and used to select a subset of the plurality of phase-locked loops. The frequencies of the selected oscillating signals generated by the selected phase-locked loops are determined and used to determine a cardiovascular pulse rate. This method can be performed a plurality of times for a respective plurality of overlapping sets of the obtained plurality of samples to determine pulse rates over time.