CN114152482A - Water-cooled supersonic-speed high-temperature gas component freezing and collecting device and method - Google Patents
Water-cooled supersonic-speed high-temperature gas component freezing and collecting device and method Download PDFInfo
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- CN114152482A CN114152482A CN202111394965.XA CN202111394965A CN114152482A CN 114152482 A CN114152482 A CN 114152482A CN 202111394965 A CN202111394965 A CN 202111394965A CN 114152482 A CN114152482 A CN 114152482A
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- 238000000034 method Methods 0.000 title claims abstract description 27
- 238000007710 freezing Methods 0.000 title claims abstract description 25
- 230000008014 freezing Effects 0.000 title claims abstract description 25
- 238000001816 cooling Methods 0.000 claims abstract description 33
- 239000000956 alloy Substances 0.000 claims abstract description 32
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 31
- 239000000523 sample Substances 0.000 claims abstract description 29
- 238000002485 combustion reaction Methods 0.000 claims abstract description 27
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 22
- 238000007789 sealing Methods 0.000 claims abstract description 21
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 8
- 238000006243 chemical reaction Methods 0.000 claims description 8
- 229910052802 copper Inorganic materials 0.000 claims description 8
- 239000010949 copper Substances 0.000 claims description 8
- 239000000498 cooling water Substances 0.000 claims description 3
- 239000008236 heating water Substances 0.000 claims description 3
- 229910000601 superalloy Inorganic materials 0.000 claims description 2
- 238000012360 testing method Methods 0.000 abstract description 13
- 230000000694 effects Effects 0.000 abstract description 4
- 238000009434 installation Methods 0.000 abstract description 4
- 239000007789 gas Substances 0.000 description 52
- 238000005259 measurement Methods 0.000 description 7
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 4
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 description 4
- 239000000446 fuel Substances 0.000 description 4
- 239000000463 material Substances 0.000 description 4
- 238000002679 ablation Methods 0.000 description 2
- 239000001569 carbon dioxide Substances 0.000 description 2
- 229910002092 carbon dioxide Inorganic materials 0.000 description 2
- 229910002091 carbon monoxide Inorganic materials 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 229910052757 nitrogen Inorganic materials 0.000 description 2
- 229910052760 oxygen Inorganic materials 0.000 description 2
- 229910001008 7075 aluminium alloy Inorganic materials 0.000 description 1
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 1
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004587 chromatography analysis Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 239000001257 hydrogen Substances 0.000 description 1
- 229910052739 hydrogen Inorganic materials 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 239000003350 kerosene Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000005057 refrigeration Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N1/00—Sampling; Preparing specimens for investigation
- G01N1/02—Devices for withdrawing samples
- G01N1/22—Devices for withdrawing samples in the gaseous state
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N1/00—Sampling; Preparing specimens for investigation
- G01N1/28—Preparing specimens for investigation including physical details of (bio-)chemical methods covered elsewhere, e.g. G01N33/50, C12Q
- G01N1/42—Low-temperature sample treatment, e.g. cryofixation
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N30/00—Investigating or analysing materials by separation into components using adsorption, absorption or similar phenomena or using ion-exchange, e.g. chromatography or field flow fractionation
- G01N30/02—Column chromatography
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N1/00—Sampling; Preparing specimens for investigation
- G01N1/02—Devices for withdrawing samples
- G01N1/22—Devices for withdrawing samples in the gaseous state
- G01N2001/2282—Devices for withdrawing samples in the gaseous state with cooling means
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- Physics & Mathematics (AREA)
- Health & Medical Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- General Physics & Mathematics (AREA)
- General Health & Medical Sciences (AREA)
- Biochemistry (AREA)
- Analytical Chemistry (AREA)
- Chemical & Material Sciences (AREA)
- Immunology (AREA)
- Pathology (AREA)
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Abstract
The invention discloses a water-cooled supersonic high-temperature gas component freezing and collecting device and a method, which relate to the technical field of ground tests of scramjet engines, and the technical scheme is as follows: comprises a main body shell; two holes with internal threads are arranged on the windward side of the main body shell at intervals; a high-temperature alloy probe is connected in the hole; the tail part of the hole is welded with an air duct, and a sealing gasket is arranged in the hole; two water-cooling circulating water pipes are arranged on the side part of the main body shell, which is on the same side as the outlet of the gas guide pipe, one end of each water-cooling circulating water pipe is an inlet, the other end of each water-cooling circulating water pipe is an outlet, and the installation positions of the two water-cooling circulating water pipes can be interchanged. The invention adopts the high-temperature alloy probe to suck supersonic high-temperature high-pressure gas, adopts the sealing gasket to ensure the sealing and heat conducting effects, introduces the gas into the collecting device through the gas guide pipe, rapidly cools the stagnant supersonic high-temperature high-pressure gas in the process, freezes the proportion of each component, and ensures the stability of the combustion product.
Description
Technical Field
The invention relates to the technical field of ground tests of scramjet engines, in particular to a water-cooled supersonic high-temperature gas component freezing and collecting device and method.
Background
In the research work of the scramjet engine, the combustion efficiency is used as an important performance judgment index, the most common method for measuring the combustion efficiency is to analyze the components of combustion products of the scramjet engine by using combusted gas, the combusted gas is usually high-temperature, high-pressure and high-speed gas, and the high-speed gas can be further heated and pressurized in the stagnation process, so that the high-temperature and high-pressure gas can further react to generate other products in the collection process, and great challenges are brought to gas collection and measurement. In order to ensure the accuracy of measurement, the problem of collecting high-temperature gas after combustion needs to be solved, and the collection process needs to rapidly cool the supersonic speed high-temperature gas in the scramjet engine tail nozzle so as to prevent the supersonic speed high-temperature gas from generating further chemical reaction.
The invention aims to solve the problems of collecting supersonic speed high-temperature and high-pressure gas after the combustion of the scramjet engine and preventing other chemical reactions which influence the measurement result due to further temperature rise and pressure rise caused by stagnation in the process, such as the further reaction of CO into CO in the stagnation process2，H2And O2Further reaction to H2O, etc., which are CO, O resulting in combustion products2And H2The inaccurate measurement of O and other components causes the inaccurate calculation of the combustion efficiency, and is also the typical situation required in the measurement of the combustion efficiencySolving the common problem.
Therefore, the invention aims to provide a water-cooling type supersonic high-temperature gas component freezing and collecting device and a method, so as to solve the problems.
The invention adopts the high-temperature alloy probe to suck supersonic high-temperature high-pressure gas, adopts the red copper sealing ring to ensure the sealing and heat conducting effects, introduces the gas into the collecting device through the gas guide pipe, rapidly cools the stagnant supersonic high-temperature high-pressure gas in the process, freezes the proportion of each component, and ensures the stability of the combustion product.
Disclosure of Invention
The invention aims to solve the problems and provides a water-cooling type supersonic high-temperature gas component freezing and collecting device and a supersonic high-temperature gas component freezing method.
The technical purpose of the invention is realized by the following technical scheme: a water-cooled supersonic high-temperature gas component freezing and collecting device comprises a main body shell, wherein a cavity is formed inside the main body shell; two holes with internal threads are formed in the windward side of the main body shell at intervals; a high-temperature alloy probe is connected in the hole; the tail part of the hole is welded with an air guide pipe positioned in the main body shell, and a sealing gasket used for sealing and connecting the high-temperature alloy probe and the air guide pipe is arranged in the hole; the outlet end of the air duct is welded with the side part of the main body shell; the lateral part of main part shell and air duct export homonymy is equipped with two way water-cooling circulating pipe, one of them one end of water-cooling circulating pipe is the entry, the other end of water-cooling circulating pipe is for exporting, and two the mounted position of water-cooling circulating pipe is interchangeable.
The invention is further configured to: the tail part of the high-temperature alloy probe is provided with external threads, and the high-temperature alloy probe is in threaded connection with a hole with internal threads on the main body shell in a screwing mode.
The invention is further configured to: the high-temperature alloy probe adopts a high alloy 3128 as a material.
The invention is further configured to: the sealing gasket is a red copper gasket and is used for sealing connection between the high-temperature alloy probe and the air guide pipe; the gas-guide tube is made of red copper.
The invention also provides a supersonic velocity high-temperature gas component freezing and collecting method, which is used for collecting by the water-cooling supersonic velocity high-temperature gas component freezing and collecting device, and the collecting method comprises the following steps: adopt the structure of device, the mounting means of main part shell cavity intracavity pipeline and cooperation superalloy probe keeps apart required cooling high-temperature gas and refrigeration cycle water, exchanges gas heat and cooling water rapidly, ensures to gather gaseous component and can not be by gathering the in-process and then rise temperature and then produce other chemical reaction because of stagnation.
The invention is further configured to: when supersonic high-temperature gas of combustion products is collected, the blockage ratio of the supersonic high-temperature gas collecting device is lower than 20% when the supersonic high-temperature gas collecting device is installed in a flow channel of a super-combustion overpressure engine, and the length-width ratio of windward projection is higher than 8.
In the scheme, the windward area of the main body shell is designed according to the size of a flow channel, the blockage ratio is lower than 20%, and the length-width ratio of the windward side is higher than 8; the material of the high-temperature alloy probe can also be comprehensively evaluated by combining the factors such as Mach number, total temperature and total pressure of incoming flow, and other high-temperature alloy materials with lower heat resistance or higher heat resistance can be replaced according to comprehensive consideration such as use requirements, cost and the like.
The invention adopts the high-temperature alloy probe to suck supersonic high-temperature high-pressure gas, adopts the red copper sealing ring to ensure the sealing and heat conducting effects, introduces the gas into the collecting device through the gas guide pipe, rapidly cools the stagnant supersonic high-temperature high-pressure gas in the process, freezes the proportion of each component, and ensures the stability of the combustion product.
In conclusion, the invention has the following beneficial effects:
1. the device is convenient for collecting products after combustion in the combustion chamber of the scramjet engine, and can ensure the stability of the components, so that the products can be used for accurately calculating the combustion efficiency;
2. the device has the advantages of simple structure, strong practicability, durability and high repeated utilization rate;
3. the device can collect high-temperature gas without using a high-temperature electromagnetic valve and a high-temperature gas storage device, and is convenient for saving the measurement and collection cost.
Drawings
FIG. 1 is a schematic sectional view of a water-cooling type supersonic high-temperature gas component freezing and collecting device in an embodiment of the invention;
FIG. 2 is a schematic sectional view of a water-cooling type supersonic high-temperature gas component freezing and collecting device in an embodiment of the invention;
FIG. 3 is a schematic installation diagram of a water-cooling supersonic high-temperature gas component freezing and collecting device in an embodiment of the invention;
FIG. 4 is a graph of gas composition data collected using the apparatus of the present invention in an example of the present invention.
In the figure: 1. a main body housing; 2. a high temperature alloy probe; 3. an air duct; 4. a water-cooling circulating water pipe; 5. sealing gaskets; 6. an aperture; 7. an internal thread; 8. and (4) external threads.
Detailed Description
The invention is described in further detail below with reference to figures 1-4.
In the scheme of the invention, the invention provides a water-cooled supersonic high-temperature gas component freezing and collecting device which comprises a main body shell 1, wherein a cavity is formed inside the main body shell 1; two holes 6 with internal threads 7 are arranged on the windward side of the main body shell 1 at intervals; the high-temperature alloy probe 2 is connected in the hole 6; the tail part of the hole 6 is welded with an air duct 3 positioned in the main body shell 1, and a sealing gasket 5 used for sealing and connecting the high-temperature alloy probe 2 and the air duct 3 is arranged in the hole 6; the outlet end of the air duct 3 is welded with the side part of the main body shell 1; two water-cooling circulating water pipes 4 are arranged on the side part of the main body shell 1 on the same side as the outlet of the gas guide tube 3, one end of each water-cooling circulating water pipe 4 is an inlet, the other end of each water-cooling circulating water pipe 4 is an outlet, and the installation positions of the two water-cooling circulating water pipes 4 can be interchanged.
The tail part of the high-temperature alloy probe 2 is provided with an external thread 8, and the high-temperature alloy probe 2 is in threaded connection with a hole 6 with an internal thread 7 on the main body shell 1 in a screwing mode.
The high-temperature alloy probe 2 adopts the Gao He 3128 (high-temperature alloy mark) as the material, and can effectively avoid ablation or deformation under the action of high-temperature air flow. Meanwhile, the high-temperature alloy probe 2 is in sealing connection with the air guide tube 3 through the sealing gasket 5, the sealing gasket 5 is a red copper gasket, heat can be effectively conducted to the position where cooling circulating water can contact, the high-temperature alloy probe 2 can exchange heat with the cooling circulating water, and ablation or deformation of the high-temperature alloy probe 2 is further avoided. The gas guide pipe 3 also adopts red copper as a material, and can rapidly exchange high-temperature gas heat with cooling circulating water due to good heat conduction performance, so that the purpose that the collected gas components cannot be heated up due to stagnation in the collection process to generate other chemical reactions is achieved.
The invention also provides a supersonic velocity high-temperature gas component freezing and collecting method, which is used for collecting by the water-cooling supersonic velocity high-temperature gas component freezing and collecting device, and the collecting method comprises the following steps: the structure of the device is adopted, and the pipeline in the cavity of the main body shell 1 and the installation mode of the high-temperature alloy probe 2 are matched, so that high-temperature gas and cooling circulating water required to be cooled are isolated, gas heat and cooling water are rapidly exchanged, and the gas collection component is ensured not to be heated up due to stagnation in the collection process to generate other chemical reactions.
When supersonic high-temperature gas of combustion products is collected, the blockage ratio of the scramjet engine is lower than 20% when the scramjet engine is installed in a flow channel of the scramjet engine, and the length-width ratio of windward projection is higher than 8, so that the scramjet engine can be guaranteed to have low total pressure loss when working, and the combustion performance of the scramjet engine is not influenced.
Example (b):
fig. 3 shows a schematic cross-sectional view of a water-cooled supersonic high-temperature gas component freezing and collecting device designed according to the scheme of the present invention and mounted on a tail nozzle of a scramjet engine of a certain type, and the other components of the device are as follows: the model number is adopted as follows: XJR6BL1-200 metal hose with diameter of 6mm is used as the connecting pipeline of the air duct 3 and the cooling circulating water pipe, a high-pressure right-angle two-position two-way electromagnetic valve of G2/2DCF10-0 is used as a control device for controlling the opening and closing of the acquisition port, and the air storage device is a 7075 aluminum alloy cylindrical air storage tank with the volume of 0.5L.
The device is applied to a ground test of a supersonic combustion chamber of a certain model, according to test requirements, incoming flow conditions of the test are Mach number Ma of 3.0, total temperature 1650k and total pressure of 1.8MPa, aviation kerosene (China-RP3) is used as fuel, the fuel injection time is 200ms, and the fuel input pressure is 2.0 MPa.
In a test, the water-cooling type supersonic velocity high-temperature gas component freezing and collecting device designed by the scheme of the invention collects and obtains combustion product gas in a tail nozzle at the downstream of a combustion chamber, and a gas component data diagram shown in figure 4 is obtained by analyzing through a chromatograph. The following are obtained through data processing and analysis: the main components of the combustion products are nitrogen, oxygen and carbon dioxide (the water content cannot be measured by chromatography) and very small amounts of hydrogen and carbon monoxide. CO 22Content of 6.62%, N276.57%, although the chromatograph cannot measure the water content, it does not affect the percentage ratio of nitrogen to carbon dioxide, and therefore the combustion efficiency measured for this train test was 75%.
In this example, in the test using the present apparatus, jet pressure of jet oil supplied from a fuel inlet was 2.0Mpa, and the test was carried on a scramjet engine ground test model in which incoming flow was mach 3.0, total temperature 1650k, and total pressure was 1.8 Mpa. In the test process, the ignition and the subsequent flame development of the engine are normal, the repeatability is good compared with the previous test result, the combustion efficiency obtained by the result measurement is 75%, the combustion efficiency range of the scramjet engine under the condition is met, and the test result is good and reliable.
The foregoing are merely examples of the present invention and common general knowledge of known specific structures and/or features of the schemes has not been described herein in any greater detail. It should be noted that, for those skilled in the art, without departing from the structure of the present invention, several changes and modifications can be made, which should also be regarded as the protection scope of the present invention, and these will not affect the effect of the implementation of the present invention and the practicability of the patent. The scope of the claims of the present application shall be determined by the contents of the claims, and the description of the embodiments and the like in the specification shall be used to explain the contents of the claims.
Claims (6)
1. A water-cooled supersonic high-temperature gas component freezing and collecting device is characterized in that: the device comprises a main body shell (1), wherein a cavity is formed inside the main body shell (1); two holes (6) with internal threads (7) are arranged on the windward side of the main body shell (1) at intervals; a high-temperature alloy probe (2) is connected in the hole (6); the tail part of the hole (6) is welded with an air guide pipe (3) positioned in the main body shell (1), and a sealing gasket (5) used for sealing and connecting the high-temperature alloy probe (2) and the air guide pipe (3) is arranged in the hole (6); the outlet end of the air duct (3) is welded with the side part of the main body shell (1); the main part shell (1) is gone up and is equipped with two way water-cooling circulating water pipe (4) with the lateral part of air duct (3) export homonymy, wherein one end of water-cooling circulating water pipe (4) is the entry, the other end of water-cooling circulating water pipe (4) is the export, and two the mounted position of water-cooling circulating water pipe (4) is interchangeable.
2. The water-cooled supersonic high-temperature gas component freezing and collecting device according to claim 1, characterized in that: the tail of the high-temperature alloy probe (2) is provided with an external thread (8), and the high-temperature alloy probe (2) is in threaded connection with a hole (6) with an internal thread (7) in the main body shell (1) in a screwing mode.
3. The water-cooled supersonic high-temperature gas component freezing and collecting device according to claim 1, characterized in that: the high-temperature alloy probe (2) is made of a high alloy 3128.
4. The water-cooled supersonic high-temperature gas component freezing and collecting device according to claim 1, characterized in that: the sealing gasket (5) is a red copper gasket and is used for sealing connection between the high-temperature alloy probe (2) and the air duct (3); the gas-guide tube (3) is made of red copper.
5. A supersonic high-temperature gas component freezing and collecting method is characterized in that: the water-cooled supersonic high-temperature gas component freezing and collecting device of any one of claims 1 to 4 is used for collecting, and the collecting method comprises the following steps: adopt the structure of device, the mounting means of main part shell (1) cavity inner tube way and cooperation superalloy probe (2) keeps apart required cooling high-temperature gas and cooling circulation water, exchanges gas heat and cooling water rapidly, ensures that the gaseous component of gathering can not be by collecting the in-process and heat up and then produce other chemical reaction because of stagnation.
6. The supersonic velocity high-temperature gas component freezing and collecting method according to claim 5, characterized in that: when supersonic high-temperature gas of combustion products is collected, the blockage ratio of the supersonic high-temperature gas collecting device is lower than 20% when the supersonic high-temperature gas collecting device is installed in a flow channel of a super-combustion overpressure engine, and the length-width ratio of windward projection is higher than 8.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111394965.XA CN114152482A (en) | 2021-11-23 | 2021-11-23 | Water-cooled supersonic-speed high-temperature gas component freezing and collecting device and method |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111394965.XA CN114152482A (en) | 2021-11-23 | 2021-11-23 | Water-cooled supersonic-speed high-temperature gas component freezing and collecting device and method |
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| CN114152482A true CN114152482A (en) | 2022-03-08 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115389213A (en) * | 2022-10-26 | 2022-11-25 | 南京理工大学 | Water-cooling multi-channel high-temperature gas pressure measuring device and method for ramjet engine |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU855425A1 (en) * | 1979-11-11 | 1981-08-15 | Предприятие П/Я М-5147 | Device for sampling chemically active high-temperature gas |
| JPH0949788A (en) * | 1995-08-08 | 1997-02-18 | Toshiba Corp | Probe for measuring gas concentration |
| CN202158978U (en) * | 2011-06-20 | 2012-03-07 | 中国航空动力机械研究所 | Gas sampling device |
| CN103398879A (en) * | 2013-05-28 | 2013-11-20 | 北京航空航天大学 | Supersonic combustion gas sampling probe |
| CN108225777A (en) * | 2017-12-27 | 2018-06-29 | 中国航发四川燃气涡轮研究院 | The high enthalpy sample probe of scramjet engine fuel gas analysis |
| RU182039U1 (en) * | 2018-04-17 | 2018-08-01 | федеральное государственное автономное образовательное учреждение высшего образования "Самарский национальный исследовательский университет имени академика С.П. Королева" | Liquid Cooled Sampler |
-
2021
- 2021-11-23 CN CN202111394965.XA patent/CN114152482A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU855425A1 (en) * | 1979-11-11 | 1981-08-15 | Предприятие П/Я М-5147 | Device for sampling chemically active high-temperature gas |
| JPH0949788A (en) * | 1995-08-08 | 1997-02-18 | Toshiba Corp | Probe for measuring gas concentration |
| CN202158978U (en) * | 2011-06-20 | 2012-03-07 | 中国航空动力机械研究所 | Gas sampling device |
| CN103398879A (en) * | 2013-05-28 | 2013-11-20 | 北京航空航天大学 | Supersonic combustion gas sampling probe |
| CN108225777A (en) * | 2017-12-27 | 2018-06-29 | 中国航发四川燃气涡轮研究院 | The high enthalpy sample probe of scramjet engine fuel gas analysis |
| RU182039U1 (en) * | 2018-04-17 | 2018-08-01 | федеральное государственное автономное образовательное учреждение высшего образования "Самарский национальный исследовательский университет имени академика С.П. Королева" | Liquid Cooled Sampler |
Non-Patent Citations (2)
| Title |
|---|
| 于洋等: "机工业务", vol. 10, 31 October 2006, 大连海事大学出版社, pages: 303 - 304 * |
| 张耀宸: "机械加工工艺设计实用手册", vol. 12, 31 December 1993, 航空工业出版社, pages: 321 - 327 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115389213A (en) * | 2022-10-26 | 2022-11-25 | 南京理工大学 | Water-cooling multi-channel high-temperature gas pressure measuring device and method for ramjet engine |
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