CN210533665U - Water-cooling light-gathering optical fiber probe for hypersonic-velocity low-density wind tunnel stable section - Google Patents
Water-cooling light-gathering optical fiber probe for hypersonic-velocity low-density wind tunnel stable section Download PDFInfo
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- CN210533665U CN210533665U CN201921976969.7U CN201921976969U CN210533665U CN 210533665 U CN210533665 U CN 210533665U CN 201921976969 U CN201921976969 U CN 201921976969U CN 210533665 U CN210533665 U CN 210533665U
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Abstract
The utility model discloses a water-cooling spotlight fiber probe for hypersonic low density wind-tunnel stable section. The optical fiber probe is characterized in that optical glass, a convex lens and an optical fiber are sequentially arranged on the axis of the optical fiber probe from front to back, and sealing rings I are arranged on two sides of the optical glass; a protective sleeve is sleeved outside the convex lens and the optical fiber, the front end of the protective sleeve tightly props against a sealing ring I behind the optical glass, and the rear end of the protective sleeve is provided with a boss; the optical glass and the protective sleeve are sleeved with the shell, a cooling water channel is arranged in the shell, the cooling water channel is connected with an external cooling water system through a cooling water connector arranged on the shell, the rear end of the shell is connected with a boss at the rear end of the protective sleeve through a connecting nut, and the boss at the rear end of the shell and the boss at the rear end of the protective sleeve are sealed through a sealing ring III; the middle part of the shell is provided with a step, and the step is sleeved with a sleeve nut. The optical fiber probe is simple in structure and high in reliability, and can lead light generated by high-temperature and high-pressure gas in the hypersonic-speed low-density wind tunnel stable section out to an optical measuring instrument.
Description
Technical Field
The utility model belongs to the technical field of the hypersonic wind tunnel test, concretely relates to water-cooling spotlight fiber probe for hypersonic low density wind tunnel stable section.
Background
In a hypersonic wind tunnel, in particular to a hypersonic low-density wind tunnel, an electric arc wind tunnel and other high-temperature high-pressure wind tunnel equipment, gas in a stable section is high-temperature high-pressure gas, and a special optical fiber probe is required to be installed when an emission spectrum or an absorption spectrum of the gas in the stable section is measured. The existing optical fiber probe is not provided with a cooling device to cause the optical fiber probe to be easily burnt, is not provided with condensing capacity to cause the optical fiber probe to have low light collection efficiency, cannot meet the measurement requirement, and needs to develop a water-cooling condensing optical fiber probe special for a hypersonic speed low-density wind tunnel stable section urgently at present.
SUMMERY OF THE UTILITY MODEL
The utility model aims to solve the technical problem that a water-cooling spotlight fiber probe for hypersonic low density wind-tunnel stable section is provided.
The utility model discloses a water-cooling spotlight fiber probe for hypersonic low density wind-tunnel stable section, its characteristics are, install optical glass, convex lens and optic fibre from the front to back on the axis of fiber probe in proper order, the sealing washer I is installed to optical glass's both sides; the convex lens and the optical fiber are sleeved with a protective sleeve, the front end of the protective sleeve is tightly propped against a sealing ring I behind the optical glass, and the rear end of the protective sleeve is provided with a boss; the optical glass and the protective sleeve are sleeved with a shell, a cooling water channel is arranged in the shell, the cooling water channel is connected with an external cooling water system through a cooling water joint arranged on the shell, the rear end of the shell is connected with a boss at the rear end of the protective sleeve through a connecting nut, and the boss at the rear end of the shell and the boss at the rear end of the protective sleeve are sealed through a sealing ring III; the middle part of the shell is provided with a step, and the step is sleeved with a sleeve nut.
The sealing ring I is a copper sealing ring or a carbon fiber sealing ring.
The optical glass is white sapphire or sapphire.
The image distance of the convex lens is positioned in the center of the front end face of the optical fiber.
The cooling water channel is an annular channel, and a guide plate parallel to the axis of the optical fiber probe is arranged in the annular channel; or the cooling water channel is a spiral channel.
The water inlet pressure range of the cooling water joint is 1 MPa-5 MPa.
The utility model discloses a guide plate that is arranged in the water-cooling spotlight fiber probe of hypersonic low density wind-tunnel stable section has the effect of cooling water conservancy diversion and improvement shell intensity.
The utility model discloses a water-cooling spotlight fiber probe for hypersonic low density wind-tunnel stable section adopts intermediate layer water-cooling mode and convex lens spotlight mode to solve the fiber probe problem of scaling loss, has improved fiber probe's light collection efficiency, can draw the light that the high temperature high-pressure gas of hypersonic low density wind-tunnel stable section that pressure is up to 10MPa, temperature up to 9000K produced to optical measurement instrument on, provide the equipment foundation for the measurement.
The utility model discloses a water-cooling spotlight fiber probe for hypersonic low density wind-tunnel stable section simple structure, the good reliability is applicable to the engineering popularization.
Drawings
FIG. 1 is a schematic structural view of a water-cooling light-gathering optical fiber probe for a stable section of a hypersonic low-density wind tunnel according to the present invention;
FIG. 2 is a schematic diagram of the structure of the cooling water channel in the water-cooled condensing optical fiber probe for the stable section of the hypersonic low-density wind tunnel of the present invention;
FIG. 3 is a mounting view (front view) of the water-cooling light-gathering fiber optic probe for the stable section of the hypersonic low-density wind tunnel of the present invention;
FIG. 4 is an installation diagram (side view) of the water-cooling light-gathering optical fiber probe for the stable section of the hypersonic low-density wind tunnel of the present invention;
in the figure, 1, a water-cooling connector 2, a flange 3, a straight water channel 4, an annular water channel 5, a test connector 6 and a water-cooling light-gathering optical fiber probe are arranged;
61. the shell 62, the sealing ring I63, the optical glass 64, the convex lens 65, the optical fiber 66, the sealing ring II 67, the sleeve nut 68, the cooling water channel 69, the cooling water joint 70, the sealing ring III 71 and the connecting nut.
Detailed Description
The present invention will be described in detail with reference to the accompanying drawings.
As shown in fig. 1, the axis of the water-cooling light-gathering optical fiber probe for the hypersonic low-density wind tunnel stable section of the present invention is sequentially provided with an optical glass 63, a convex lens 64 and an optical fiber 65 from front to back, and two sides of the optical glass 63 are provided with a sealing ring i 62; a protective sleeve is sleeved outside the convex lens 64 and the optical fiber 65, the front end of the protective sleeve tightly props against a sealing ring I62 behind the optical glass 63, and the rear end of the protective sleeve is provided with a boss; the optical glass 63 and the protective sleeve are sleeved with a shell 61, a cooling water channel 68 is arranged in the shell 61, the cooling water channel 68 is connected with an external cooling water system through a cooling water joint 69 arranged on the shell 61, the rear end of the shell 61 is connected with a boss at the rear end of the protective sleeve through a connecting nut 71, and the boss at the rear end of the shell 61 and the boss at the rear end of the protective sleeve are sealed through a sealing ring III 70; the middle part of shell 61 is provided with the step, and step department cover is equipped with cap nut 67.
The sealing ring I62 is a copper sealing ring or a carbon fiber sealing ring.
The optical glass 63 is made of white sapphire or sapphire.
The image distance of the convex lens 64 is located at the center of the front end face of the optical fiber 65.
As shown in fig. 2, the cooling water channel 68 is an annular channel, and a guide plate parallel to the axis of the water-cooling light-gathering fiber probe is arranged in the annular channel; alternatively, the cooling water passage 68 may be a spiral passage.
The water inlet pressure of the cooling water joint 69 is 1 MPa-5 MPa.
Example 1
This embodiment will the utility model discloses a water-cooling spotlight fiber probe for hypersonic low density wind-tunnel stable section installs on water-cooling test flange.
As shown in fig. 3, the water-cooling test flange comprises a water-cooling joint 1, a flange 2, a straight water channel 3, an annular water channel 4 and a test joint 5;
the flange 2 is a circular ring, a cavity in the center of the circular ring is used for passing through hypersonic low-density wind tunnel airflow, an annular water channel 4 is arranged in the ring wall of the circular ring, two uniformly distributed straight water channels 3 perpendicular to the annular water channel 4 are arranged on the annular water channel 4, the straight water channels 3 are connected with water-cooling joints 1, one water-cooling joint 1 is externally connected with a cooling water inlet pipeline, and the other water-cooling joint 1 is externally connected with a cooling water outlet pipeline; bolt holes used for connecting and fixing the hypersonic speed low-density wind tunnel stabilizing section are uniformly distributed in the ring wall of the ring, a boss is arranged on one side of the outer surface of the ring wall of the ring, a corresponding concave platform is arranged on the other side of the outer surface of the ring wall of the ring, an annular sealing groove is formed in the boss, a sealing ring is installed in the annular sealing groove, and the boss and the concave platform are used for positioning and sealing when the water-cooling test flange is connected with the hypersonic speed low-density wind tunnel stabilizing section.
The thickness range of the circular ring of the flange 2 is 20 mm-50 mm.
The water-cooling joint 1, the flange 2 and the test joint 5 are made of stainless steel.
The water inlet pressure range of the water-cooling joint 1 is 1 MPa-5 MPa.
Two through holes which are uniformly distributed and vertical to the annular water channel 4 are also formed in the annular water channel 4, and the through holes are connected with test joints 5; the test joint 5 is connected with the water-cooling light-gathering optical fiber probe 6 through a sleeve nut 67, and the joint is sealed by a sealing ring II 66.
If the emission spectrum needs to be measured, one water-cooling light-gathering optical fiber probe 6 is plugged by a blind plate, the optical fiber 65 of the other water-cooling light-gathering optical fiber probe 6 is connected with an external spectrometer, and an emission spectrum is obtained through a CCD camera.
If the absorption spectrum needs to be measured, connecting the optical fiber 65 of one water-cooling light-gathering optical fiber probe 6 with an external laser, wherein the laser provides an incident light source; the optical fiber 65 of the other water-cooling light-gathering optical fiber probe 6 is connected with an external spectrometer, and an absorption spectrogram is obtained through a CCD camera.
Claims (6)
1. A water-cooling light-gathering optical fiber probe for a hypersonic-speed low-density wind tunnel stabilization section is characterized in that optical glass (63), a convex lens (64) and an optical fiber (65) are sequentially arranged on the axis of the optical fiber probe from front to back, and sealing rings I (62) are arranged on two sides of the optical glass (63); a protective sleeve is sleeved outside the convex lens (64) and the optical fiber (65), the front end of the protective sleeve tightly props against a sealing ring I (62) behind the optical glass (63), and the rear end of the protective sleeve is provided with a boss; a shell (61) is sleeved outside the optical glass (63) and the protective sleeve, a cooling water channel (68) is arranged in the shell (61), the cooling water channel (68) is connected with an external cooling water system through a cooling water joint (69) arranged on the shell (61), the rear end of the shell (61) is connected with a boss at the rear end of the protective sleeve through a connecting nut (71), and the rear end of the shell (61) is sealed with the boss at the rear end of the protective sleeve through a sealing ring III (70); the middle part of the shell (61) is provided with a step, and a sleeve nut (67) is sleeved at the step.
2. The water-cooling light-gathering optical fiber probe for the hypersonic-velocity low-density wind tunnel stabilizing section as claimed in claim 1, wherein the sealing ring I (62) is a copper sealing ring or a carbon fiber sealing ring.
3. The water-cooled condensing optical fiber probe for the stabilizing section of the hypersonic low-density wind tunnel according to claim 1, wherein the optical glass (63) is sapphire or sapphire.
4. The water-cooled condensing optical fiber probe for the stabilizing section of the hypersonic low-density wind tunnel according to claim 1, wherein the image distance of the convex lens (64) is located at the center of the front end face of the optical fiber (65).
5. The water-cooling light-gathering optical fiber probe for the stabilizing section of the hypersonic-speed low-density wind tunnel according to claim 1, wherein the cooling water channel (68) is an annular channel, and a guide plate parallel to the axis of the optical fiber probe is arranged in the annular channel; or the cooling water channel (68) is a spiral channel.
6. The water-cooling light-gathering optical fiber probe for the hypersonic low-density wind tunnel stabilizing section as claimed in claim 1, wherein the water inlet pressure range of the cooling water joint (69) is 1 MPa-5 MPa.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921976969.7U CN210533665U (en) | 2019-11-15 | 2019-11-15 | Water-cooling light-gathering optical fiber probe for hypersonic-velocity low-density wind tunnel stable section |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921976969.7U CN210533665U (en) | 2019-11-15 | 2019-11-15 | Water-cooling light-gathering optical fiber probe for hypersonic-velocity low-density wind tunnel stable section |
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| CN210533665U true CN210533665U (en) | 2020-05-15 |
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| CN201921976969.7U Active CN210533665U (en) | 2019-11-15 | 2019-11-15 | Water-cooling light-gathering optical fiber probe for hypersonic-velocity low-density wind tunnel stable section |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110715789A (en) * | 2019-11-15 | 2020-01-21 | 中国空气动力研究与发展中心超高速空气动力研究所 | Water-cooling light-gathering optical fiber probe for hypersonic-velocity low-density wind tunnel stable section |
| CN113959675A (en) * | 2021-12-14 | 2022-01-21 | 中国空气动力研究与发展中心超高速空气动力研究所 | Optical probe for identifying flow partition characteristics of acceleration section of expansion wind tunnel |
-
2019
- 2019-11-15 CN CN201921976969.7U patent/CN210533665U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110715789A (en) * | 2019-11-15 | 2020-01-21 | 中国空气动力研究与发展中心超高速空气动力研究所 | Water-cooling light-gathering optical fiber probe for hypersonic-velocity low-density wind tunnel stable section |
| CN113959675A (en) * | 2021-12-14 | 2022-01-21 | 中国空气动力研究与发展中心超高速空气动力研究所 | Optical probe for identifying flow partition characteristics of acceleration section of expansion wind tunnel |
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