6results about How to "Reduce wall temperature" patented technology

The invention is suitable for the technical field of aero-engines, and provides a venturi tube structure, a swirler and a combustion chamber, the venturi tube structure comprises a venturi tube outer layer and a venturi tube inner layer, the venturi tube outer layer is provided with a containing cavity, a plurality of first protrusions are arranged on one side of the venturi tube inner layer in the circumferential direction at intervals, and a plurality of second protrusions are arranged on the other side of the venturi tube inner layer in the circumferential direction at intervals; the venturi tube inner layer is embedded in the containing cavity, the multiple first protrusions abut against the inner wall of the containing cavity so that a first cavity can be formed between the venturi tube outer layer and the venturi tube inner layer, and the multiple second protrusions abut against the inner wall of the containing cavity so that a second cavity can be formed between the venturi tube outer layer and the venturi tube inner layer; the first cavity and the second cavity are mutually independent and are used for preventing high temperature from being directly transmitted to the inner layer of the venturi tube. By means of the core structure design of the double-layer tube body and the independent cavities, the first cavity and the second cavity which are independent of each other are formed between the two tubes, direct conduction of high temperature from the outer layer of the venturi tube to the inner layer of the venturi tube is blocked by means of the air heat insulation characteristic, and the carbon deposition restraining effect is remarkable.

This invention relates to a microribbed jet impact cooling channel for hot-end components of aircraft. It is an integral structure comprising 1 to 100 sub-channels arranged side-by-side, with adjacent sub-channels sharing sidewalls. Each sub-channel includes a main channel, microribs, and jet holes. Fuel enters the main channel from one end and through the jet holes, exiting from the other end. The main channel has a rectangular cross-section. Microribs are arranged at the bottom of the main channel, forming an array of microribs. Jet holes are arranged at the top of the main channel, with uniform or non-uniform distribution. The sidewalls of the main channel are smooth planes. This invention, with its arrayed microribs and jet holes, couples the effects of the microribs and the jet impact, effectively reducing the wall temperature of the scramjet engine combustion chamber without adding extra mass, effectively suppressing the temperature rise of high-heat components in the aircraft, thereby achieving higher Mach numbers.

The application provides a combustion chamber wall surface with locally encrypted cooling holes and a swirl combustion chamber, and comprises a combustion chamber wall surface; a plurality of cooling holes are arranged on the combustion chamber wall surface, and the cooling holes are distributed according to a temperature distribution curve of the combustion chamber wall surface. According to the application, the plurality of cooling holes are distributed according to the temperature distribution curve of the combustion chamber wall surface, the spacing between the cooling holes and adjacent holes is directly related to the local temperature, the cooling holes are denser in the place with higher temperature, the cooling effect is improved, the wall surface temperature is reduced, and the generation of local high temperature is avoided.

The present application relates to a kind of double-wall heat shields with baffle sandwich structure, double-wall heat shield is gas film orifice plate and impact orifice plate and turbulence baffle structure jointly constitutes the double-wall heat shield described;Turbulence baffle structure includes first helical baffle and second helical baffle vertically arranged on gas film orifice plate, and multiple separate turbulence spaces are enclosed by two baffle plates crossing each other;Gas film orifice is arranged at the multiple intersection points formed by the first helical baffle and the second helical baffle on the gas film orifice plate;The present application also provides the heat shield gas film forming method, airflow flows out through multiple fan-shaped holes to form gas film outflow and main flow gas mixing, and forms gas film cover layer on wall surface;The present application can not only strengthen the heat exchange inside heat shield, but also improve gas film cold efficiency, in addition, the impact orifice plate-gas film orifice plate double-wall structure with baffle turbulence fixed has good mechanical properties.

The application discloses a mixing hopper which is arranged on the wall of a flame tube, and comprises an inner cone part, an outer ring part arranged outside the inner cone part, and a hopper cap used for connecting the wall of the flame tube. The inner cone part and the hopper cap enclose a mixing cavity used for mixing high-temperature gas and cooling gas flow. The inner cone part and the outer ring part enclose a cooling gap used for the flow of the cooling gas flow. Cooling holes are arranged on the inner cone part and are respectively communicated with the mixing cavity and the cooling gap, and are used for introducing the cooling gas flow into the cooling gap to impact cool the outer ring part and form a cooling gas film on the inner cone part. The outer ring part actively uses a small amount of cooling gas flow in cooperation with the cooling holes to effectively reduce the wall temperature of the mixing hopper and prevent the mixing hopper from ablation. Meanwhile, the outer ring part can also shield part of the wall of the inner cone part to prevent the inner cone part from ablation as much as possible, and the cooling effect is good, the service life of the mixing hopper is prolonged, and the mixing hopper can be used in the flame tube for a long time. In addition, the application further discloses a combustion chamber. In addition, the application further discloses an aero-engine.