摘要:
A system may include a controller configured to cause a capacitance probe to subject a material to a first electric signal having a first frequency and determine a first capacitance of the material at the first frequency. The controller is configured to cause the capacitance probe to subject the material to a second electric signal at a second frequency and determine a second capacitance of the material at the second frequency. The material includes at least a first constituent phase and a second constituent phase. The first constituent phase and the second constituent phase have substantially similar dielectric constants at the first frequency and substantially different dielectric constants at the second frequency. The controller is further configured to determine a porosity of the material based on the first capacitance and determine a relative phase composition of the first constituent phase and the second constituent phase based on the second capacitance.
摘要:
An apparatus is disclosed that includes a gas turbine engine including a first rotor blade axially adjacent a second rotor blade and an aperture formed in one of the first rotor blade and the second rotor blade and structured to emit a fluid therefrom. A fluid source is in flow communication with the aperture and configured to flow the fluid through the aperture.
摘要:
A control for a hybrid turbo electric aero-propulsion system prioritizes and optimizes the operating parameters, according to a desired optimization objective, for and across a number of different control optimization subsystems of the hybrid turbo electric aero-propulsion system. The control subsystems may include, for example, a propulsion control optimization subsystem and a power plant control optimization subsystem. The optimizations may be based on a system model, which is developed and updated during the operation of the hybrid turbo electric aero-propulsion system.
摘要:
A system and a method for nondestructive testing of a component (12), e.g. a gas turbine engine blade, on a movable stage (26) in an inspection station (11) is disclosed. It includes providing a heat pulse to the exterior of the component (12), e.g. by flashing the component using a flash lamp (20) configured for flash thermography. It further includes collecting first image data regarding the component (12) using an infrared camera (14), flowing a fluid, e.g. cooling air, from a fluid supply (22) through the component (12), and collecting second image data regarding the component (12) using the infrared camera (14).
摘要:
A novel ceramic matrix composite is disclosed for forming components that are operable in high temperature environments such those in gas turbine engines and the like. The ceramic matrix composite can include at least one layer of non-crimped fibers positioned substantially parallel to one another. A relatively small diameter elastic fiber can be constructed to stitch the non-crimped fibers together and a ceramic matrix may be deposited around the at least one layer of non-crimped fibers.
摘要:
One embodiment of the present disclosure is a unique gas turbine engine. Another embodiment of the present disclosure is a unique machine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and electrical systems.
摘要:
A containment system for a gas turbine engine includes a fan track assembly for use with a containment case. The fan track assembly includes a body of collapsible material that is positioned within a cavity of the fan case, and voids are provided for providing space in the event of a catastrophic blade failure. Various configurations of the fan track liner assembly are provided along with various mounting methodologies for securing the track liner assembly to the fan case of a gas turbine engine.
摘要:
A seal for use in a machine, such as a machine with rotating members, includes a labyrinth seal with multiple fins. The seal is slotted and is designed to limit fluid flow to the desired amount from the high pressure side of the seal to the low pressure side of the seal inside partially or exclusively radially extending cavities between two rotating members. The rotating members may operate at different speeds with a common axis of rotation. The seal remains effective when the rotating members move axially in relation to one another despite the fins having a component parallel to the axis of rotation.
摘要:
A method of assembling a gas turbine engine comprising the steps of providing a casing having an insertion aperture in its outer surface. A guide vane is inserted through the insertion aperture. The guide vane is secured to the outer surface of the casing such that the guide vane can be serviced from an outer part of the casing. A corresponding gas turbine engine is also provided.
摘要:
A gas turbine engine device is disclosed for mixing fuel and air prior to a combustion. The device includes a pilot mixer (60) and a main mixer (62) each having a fuel opening (88, 68) for the delivery of fuel to one or more passages. In one form the main mixer includes an inner passage (74) and an outer passage (76) and in which a fuel opening delivers fuel to the inner passage (74). The main mixer (62) can include swirlers in the inner and/or outer passages. The pilot mixer (60) can also include a swirler (66). In one embodiment the main mixer (62) includes a converging flow path and/or a diverging flow path. The pilot mixer (60) can also include a converging and/or diverging flow path and in one form is sheltered from an exit of the device. The main mixer fuel opening (88) can be disposed between an upstream end and a downstream end of the mixer.