Sink-air film hole cooling structure for cooling blades and air film cooling device
A technology for cooling blades and cooling structures, which is applied to parts of pumping devices for elastic fluids, supporting elements of blades, non-variable pumps, etc., which can solve the problem of air film hole air flow turbulent kinetic energy enhancement and lower external surface Problems such as film cooling performance, flow separation and backflow blockage can be solved to achieve the effect of improving film cooling performance, excellent cooling performance, and flow vortex suppression
Inactive Publication Date: 2017-10-13
SHANGHAI JIAO TONG UNIV
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Problems solved by technology
Conventional film cooling holes are directly connected to the wall of the internal channel. When the airflow in the internal channel flows through the film cooling hole, it is easy to generate flow separation and vortex at the entrance of the film hole, and due to the influence of the pressure difference between the inside and outside of the film hole Backflow is formed in the gas film hole, these factors have a blocking effect on the gas film hole and have a significant adverse effect on the film cooling performance, which is reflected in the following aspects: (1) due to the flow separation and backflow in the gas film hole to form a blockage effect, which will reduce the cooling air flow in the air film hole, thereby directly reducing the air film cooling performance; (2) The flow attachment of the air film orifice and the flow vortex in the air film hole increase the turbulent kinetic energy of the air flow in the air film hole. It will enhance the mixing effect of the air film hole outflow and the high temperature gas outside, thereby reducing the film cooling effect
In particular, when the flow in the inner channel is reversed to the external main flow, the current air film hole inlet and the air film hole are prone to form large-scale flow vortices and backflows, which block the air film outlet flow and greatly reduce the outer surface air film cooling performance
Method used
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[0036] Such as Figure 1~4 As shown, a preferred embodiment of the present invention provides a film cooling device, including a cooling blade 1, one or more depressions 2, and one or more film holes 3, wherein the depression 2 is arranged on the cooling blade 1 The inner wall 11 of the air film hole runs through the cooling blade 1, and the air film hole 3 has an entrance, and the entrance of all the air film holes 3 is located at the depression 2; or the entrance of a part of the air film hole 3 is located at the depression 2, and the other part of the air film hole The inlet of 3 is located on the inner wall surface 11 of the cooling blade 1 except for the recess 2 ; or a plurality of air film holes 3 are located at one recess 2 . The above-mentioned depression 2 and the film hole 3 located at the depression 2 constitute a depression-film hole cooling structure.
[0037] In this embodiment, when the entrance of the air film hole 3 is located at the depression 2, a part of ...
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The invention discloses a sink-air film hole cooling structure for cooling blades. The sink-air film hole cooling structure comprises sinks arranged on the inner walls of the cooling blades and air film holes penetrating the cooling blades, and each air film hole is provided with an inlet which is located at the corresponding sink. The invention further discloses an air film cooling device which comprises the cooling blades, one or more sinks and one or more air film holes, wherein the sinks are arranged on the inner walls of the cooling blades, the air film holes penetrate the cooling blades, the air film holes are provided with inlets, and the inlets of all air film holes are located at the sinks; or the inlets of parts of the air film holes are located at the sinks, and the inlets of the other parts of the air film holes are located in zones, without the sinks, of the inner wall faces of the cooling blades; or the inlets of the multiple air film holes are located at one sink. By means of the sink-air film hole cooling structure, matching between the air film holes and runners inside the cooling blades can be improved, and therefore the flowing state at the inlets of the air film holes and inside the air film holes is improved, and the air film cooling performance of the external wall faces of the cooling blades is improved.
Description
technical field [0001] The invention relates to the technical field of cooling high-temperature components of gas turbines or aeroengines, in particular to a recess-film hole cooling structure and a film cooling device for cooling blades. Background technique [0002] Air film cooling is of great significance for the thermal protection of high temperature components of gas turbines / aeroengines, such as cooling of turbine blades and cooling of combustion chambers. Air film cooling usually obtains cooling air from the internal cooling channel of the turbine blade. The air film hole runs through the wall of the turbine blade, and the film cooling hole connects the internal cooling channel of the turbine blade with the outer surface. Therefore, the airflow in the inner cooling channel flows out to the outer surface through the film holes, and spreads as far as possible on the outer surface, thereby isolating the outer hot air flow from the surface of the turbine blade and provid...
Claims
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Login to View More IPC IPC(8): F01D5/18F04D29/66
CPCF01D5/186F04D29/667
Inventor 饶宇李彦霖张鹏
Owner SHANGHAI JIAO TONG UNIV