33results about How to "Reduce the difficulty of production technology" patented technology

The present invention discloses multi-function layer nitride low radiation energy saving glass, the multi-function layer nitride low radiation energy saving glass includes a coated glass substrate (1), a depositing barrier layer for Na + ion barrier, a first functional layer, a second functional layer, a third functional layer and a protective layer are arranged sequentially from the inside to the outside on the coated glass substrate (1); the depositing barrier layer is a silicon nitride film layer (2); the first functional layer comprises three continuous film layers, namely an aluminum nitride layer (31), a titanium nitride film layer or a metal titanium film layer (32), and an aluminum nitride film layer (33); the second functional layer is a zirconium nitride film layer (41); the third functional layer is an aluminum nitride film layer (51), a titanium nitride film layer (52) and an aluminum nitride film layer (53); and the protective layer is a silicon nitride film layer (61). The multi-function layer nitride low radiation energy saving glass is good in weather resistance, good in corrosion resistance, good in mechanical properties, uniform in film layer distribution, softer in colors, and good in film density.

An energy-saving air-draught coal - fired range is prepared by connecting coal - fired range, draught tube, exhaust-heat boiler and draught fan in series. The device works totally in semi-closed draught mode to let air flow under internal draft condition so there is no dust in the room and the surplus flame and heat are led to exhaust heat boiler so energy saving purpose can be achieved.

The invention relates to a gravity heat transfer device and a preparation method thereof. The gravity heat transfer device includes a heat transfer device body and a liquid working medium, the heat transfer device body includes a heat transfer device shell and a separation layer, and the separation layer covers the inner wall of the heat transfer device casing; its preparation method The steps are: manufacturing a heat transfer shell with openings at both ends; performing surface treatment on the inner surface of the heat transfer shell to reduce surface energy; sealing the surface-treated heat spreader shell by welding side, and reserve a liquid injection hole at any position of the heat transfer shell; inject the liquid working medium into the inner cavity of the heat transfer device through the liquid injection hole; pump out the air in the inner cavity of the heat transfer device to form a vacuum; close the liquid injection hole . The gravity heat transfer device of the present invention has high heat transfer density, good temperature uniformity, simple structure, light weight, high reflux efficiency after liquid working medium is condensed, and the preparation method is simple in process and convenient in operation.

The invention discloses an ultraviolet detector based on a ZnO nanorod / micro-nano fiber hybrid waveguide. The ultraviolet detector includes sequentially connected light source, input single-mode fiber, ZnO nanorod / micro-nano fiber hybrid waveguide, output single-mode fiber, spectrometer; the ZnO nanorod / micro-nano fiber hybrid waveguide is prepared by fusion tapered method The micro-nano optical fiber is further realized by growing zinc oxide nanorods in the prepared micro-nano optical fiber cone region by hydrothermal method; when the ZnO nanorod / micro-nano optical fiber hybrid waveguide is irradiated by ultraviolet light, the refractive index of the zinc oxide nano-rods changes , and then the evanescent field in the taper region of the micro-nano fiber changes accordingly, thereby changing the output light intensity of the ZnO nanorod / micro-nano fiber hybrid waveguide. The invention also discloses a corresponding manufacturing method of the ultraviolet detector based on the ZnO nanorod / micro-nano fiber hybrid waveguide. The invention realizes all-fiber ultraviolet detection based on the evanescent field principle, and has high sensitivity, compact and simple structure, and strong anti-electromagnetic interference capability.

The invention discloses a novel high-pressure turbine of an aircraft engine. The novel high-pressure turbine comprises a plurality of turbine blades and a turbine disc, wherein a plurality of wedged grooves are formed in an outer side of the turbine disc at intervals; each wedged groove is internally provided with a wedged key, and a gap is formed between each wedged groove and the corresponding wedged key; the outer side of each wedged key is connected with two turbine blades; the outer side of each turbine blade is fixedly connected with an inner side of a turbine hoop and is limited by the turbine hoop. The turbine blades are connected with the inner side of the turbine hoop and the turbine blades are not connected with the turbine disc. In a working process, a centrifugal force of the turbine blades falls onto the turbine hoop and the turbine blades completely bear compressive stress, so that a situation that turbine blades of a traditional turbine only bear tensile stress is changed; sufficient condition guarantees are provided for popularization and application of a full-ceramic turbine blade. A combination form of the turbine blades and the turbine disc provides a sufficient free expansion space for heating of the turbine blades and heat stress of the turbine blades is reduced at maximum; impact, caused by vibration, on a turbine shaft can also be alleviated and the service life of the aircraft engine is prolonged.