Abstract: A turbine blade having a gas film cooling structure with a composite irregular groove. The turbine blade has a hollow structure, and a plurality of first grooves which are recessed grooves are provided on an outer surface thereof. A plurality of discrete holes A extending to an inner surface of the turbine blade are provided at the groove bottom of each first groove. The first groove is an irregular groove, and includes at least two portions in a depth direction. A portion having a depth H1 from the groove bottom of the first groove is a first portion, and the rest thereof is a second portion. At least one side surface of the second portion is formed by expanding in lateral direction from a corresponding side surface of the first portion.

Abstract: A laser processing head (100) comprises a first-level nozzle (110) and a second-level nozzle (120) that communicate with each other, wherein the second-level nozzle (120) is arranged downstream of the first-level nozzle (110); an inner diameter of the second-level nozzle (120) gradually decreases in a laser transmission direction, and minimum inner diameter of the first-level nozzle (110) is larger than the inner diameter of a tail end of the second-level nozzle (120). The laser processing head (100) solves the contradiction between high energy density laser and the system reliability through gradual coupling. Also provided are a laser processing system and a laser processing method.

Abstract: A turbine blade having a gas film cooling structure with a composite irregular groove. The turbine blade has a hollow structure, and a plurality of first grooves which are recessed grooves are provided on an outer surface thereof. A plurality of discrete holes A extending to an inner surface of the turbine blade are provided at the groove bottom of each first groove. The first groove is an irregular groove, and includes at least two portions in a depth direction. A portion having a depth H1 from the groove bottom of the first groove is a first portion, and the rest thereof is a second portion. At least one side surface of the second portion is formed by expanding in lateral direction from a corresponding side surface of the first portion.

Abstract: Disclosed are the thermal protection and drag reduction method and system for an ultra high-speed aircraft. A cold source is and a cold source driving device are arranged inside a cavity of the ultra high-speed aircraft. A plurality of micropores are arranged on a wall surface of the cavity. The cold source driving device comprises an air pump, a cold source reservoir and a buffer. The air pump supplies compressed air to a cold source reservoir during operation. The cold source enters the buffer and is vaporized under the action of air pressure. High-pressure gas is ejected from the micropores to form a gas film on the outer surface of the cavity. The gas film not only can perform thermal protection on the ultra high-speed aircraft, but also can effectively reduce viscous drag between the aircraft and the external gas, by virtue of which the thermal barrier phenomenon is alleviated or eliminated. Therefore, security of the ultra high-speed aircraft is improved and service life is prolonged.

Abstract: A laser processing head (100) comprises a first-level nozzle (110) and a second-level nozzle (120) that communicate with each other, wherein the second-level nozzle (120) is arranged downstream of the first-level nozzle (110); an inner diameter of the second-level nozzle (120) gradually decreases in a laser transmission direction, and minimum inner diameter of the first-level nozzle (110) is larger than the inner diameter of a tail end of the second-level nozzle (120). The laser processing head (100) solves the contradiction between high energy density laser and the system reliability through gradual coupling. Also provided are an application of the laser processing head, a laser processing system and a laser processing method.

Abstract: Acoustic logging data are obtained using a logging tool including at least on transmitter and a plurality of receivers. A waveform matching inversion is performed to obtain formation slowness profiles at various resolutions ranging from the total length of the receiver array to the inter-array receiver spacing. Using overlapping sub-arrays of reduced aperture provides for resolution enhancement. The enhancement is achieved by minimizing the noise contamination effects by maximizing the information redundancy in waveform data. The method achieves this by isolating the wave event of interest and matching the waveform of the event for all possible receiver pairs allowed by the sub-array. The high-resolution slowness curve successfully resolves the laminated features in a geological formation. This invention is a useful tool for evaluating thin beds in laminated formations using borehole acoustic logging.