Optical observation device for flow direction cross section of supersonic combustion chamber inner flow field
A supersonic combustion chamber and observation device technology, which is applied to the safety device of the combustion chamber, combustion chamber, combustion method, etc., can solve the problems of low shooting frequency, structural strength and air tightness of the supersonic combustion chamber, and achieve optimal size design Effect
Pending Publication Date: 2021-04-16
NAT UNIV OF DEFENSE TECH
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However, this existing technology not only affects the structural strength and airtightness of the supersonic combustion chamber after the introduction of the observation window, but also requires shooting from the side and then using image correction methods to obtain the flow section, and the shooting frequency is also very low
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[0023] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.
[0024] It should be noted that all directional indications (such as up, down, left, right, front, back...) in the embodiments of the present invention are only used to explain the relationship between the components in a certain posture (as shown in the accompanying drawings). Relative positional relationship, movement conditions, etc., if the specific posture changes, the directional indication will also change accordingly.
[0025] In addition, in t...
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The invention discloses an optical observation device for a flow direction cross section of a supersonic combustion chamber inner flow field. The device comprises a combustion chamber which consists of an isolation segment, a concave cavity and an expansion segment which are sequentially connected, an endoscope lens with the lens end located in the isolation segment and facing the concave cavity and the lens base end located outside the combustion chamber, a light guide pipe internally provided with a light guide channel, and a camera, wherein the lens base end of the endoscope lens is connected to the position, corresponding to one end of the light guide channel, of the light guide pipe in an embedded mode, and a lens of the camera is connected to the position, corresponding to the other end of the light guide channel, of the light guide pipe in an embedded mode. The endoscope lens is arranged on the isolation segment, and the light guide channel in the light guide pipe enables the camera to image the cross section of the supersonic combustion chamber inner flow field, so that the optical observation of the cross section of the inner flow field is realized, on the premise that a glass observation window is not arranged, optical observation of a cold-state flow field and a combustion flow field of the transverse section of the supersonic combustion chamber inner flow field can be conducted, and meanwhile large flow field interference cannot be caused.
Description
technical field [0001] The invention relates to the technical field of flow field observation in a supersonic combustion chamber, in particular to an optical observation device for a flow direction section of a flow field in a supersonic combustion chamber. Background technique [0002] Traditional observation of the flow field in a supersonic combustor with a rectangular cross-section requires the design of an observation window in the combustion chamber, while observing the flow field in a supersonic combustor with a circular cross-section even if a circular observation window is used, it cannot be clearly imaged due to the optical refraction distortion of the circular glass question. For example, in the (Acta Astronautica, 152 (2018) 752–756) paper, by setting a glass observation window in the supersonic combustion chamber with a rectangular cross section, placing the high-speed camera and the supersonic combustion chamber at a certain angle, combined with the method of i...
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Login to View More IPC IPC(8): F23M11/04
CPCY02T50/60
Inventor 蔡尊匡孝波朱家健孙明波
Owner NAT UNIV OF DEFENSE TECH