CN117090709A - Layered supersonic air film cooling single-wall spray pipe extension section - Google Patents
Layered supersonic air film cooling single-wall spray pipe extension section Download PDFInfo
- Publication number
- CN117090709A CN117090709A CN202311026501.2A CN202311026501A CN117090709A CN 117090709 A CN117090709 A CN 117090709A CN 202311026501 A CN202311026501 A CN 202311026501A CN 117090709 A CN117090709 A CN 117090709A
- Authority
- CN
- China
- Prior art keywords
- air film
- supersonic
- speed air
- supersonic speed
- section
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 239000007921 spray Substances 0.000 title claims abstract description 52
- 238000001816 cooling Methods 0.000 title claims abstract description 23
- 239000002826 coolant Substances 0.000 claims abstract description 50
- 238000005507 spraying Methods 0.000 claims abstract description 35
- 239000007789 gas Substances 0.000 claims description 24
- 230000008602 contraction Effects 0.000 claims description 11
- 238000009826 distribution Methods 0.000 claims description 5
- 239000002737 fuel gas Substances 0.000 claims description 4
- 230000000087 stabilizing effect Effects 0.000 claims description 3
- 238000000034 method Methods 0.000 abstract description 7
- 239000011248 coating agent Substances 0.000 abstract description 5
- 238000000576 coating method Methods 0.000 abstract description 5
- 239000012720 thermal barrier coating Substances 0.000 abstract description 3
- 238000003466 welding Methods 0.000 abstract description 2
- 239000010410 layer Substances 0.000 description 13
- 239000000463 material Substances 0.000 description 6
- 230000003068 static effect Effects 0.000 description 5
- 230000000694 effects Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 229910001080 W alloy Inorganic materials 0.000 description 2
- GAYPVYLCOOFYAP-UHFFFAOYSA-N [Nb].[W] Chemical compound [Nb].[W] GAYPVYLCOOFYAP-UHFFFAOYSA-N 0.000 description 2
- 239000002131 composite material Substances 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000004907 flux Effects 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 230000002238 attenuated effect Effects 0.000 description 1
- 230000004323 axial length Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 239000002356 single layer Substances 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/97—Rocket nozzles
Abstract
A layered supersonic speed air film cooling single-wall spray pipe extension section comprises a supersonic speed air film spraying device and a single-wall spray pipe extension section; the supersonic speed air film spraying device is of an annular structure, one end of the supersonic speed air film spraying device is welded with the upper section of the spray pipe, and the other end of the supersonic speed air film spraying device is welded with the extension section of the single-wall spray pipe; the outer side of the annular structure is provided with a hole to serve as a coolant inlet, a closed annular cavity is formed between the annular structure and the upper section of the spray pipe after welding, and the annular cavity serves as a coolant inlet collector; two circles of supersonic speed air film holes are arranged at one end, close to the extension section of the single-wall spray pipe, of the supersonic speed air film spraying device, and the supersonic speed air film holes are respectively an inner circle of supersonic speed air film holes and an outer circle of supersonic speed air film holes. According to the invention, the coolant forms a layered air film through the inner and outer rows of supersonic air film holes, so that the highest wall surface temperature of the extension section of the single-wall spray pipe is effectively reduced. Meanwhile, the complex processes such as high-emissivity coating, thermal barrier coating and the like are avoided, and the risk caused by easy falling of the coating is avoided.
Description
Technical Field
The invention belongs to the field of liquid rocket engines, and relates to a layered supersonic air film cooling single-wall spray pipe extension section.
Background
In order to obtain higher performance, the liquid rocket engine of the upper stage usually adopts a jet pipe with a larger area ratio, the heat flux density of the wall surface of the jet pipe at the downstream of the throat part of the engine is gradually reduced, the heat protection requirement is correspondingly weakened, the jet pipe of the engine of the upper stage usually adopts a segmented structure, the jet pipe extension section adopts a single-layer thin-wall structure (single-wall jet pipe extension section) cooled by combining radiation and supersonic air films, and common materials of the single-wall jet pipe extension section comprise nickel-based alloy capable of resisting high temperature of about 1000 ℃, niobium-tungsten alloy capable of resisting high temperature of about 1500 ℃ and composite material capable of resisting high temperature of more than 1800 ℃, and the cost of the niobium-tungsten alloy and the composite material is high and the manufacturing process is complex. The coolant is sprayed out through a plurality of small shrinkage-expansion spray pipes which are positioned close to the wall surface, so that an extended section of the downstream single-wall spray pipe is protected by an attached supersonic cooling air film.
However, in the conventional supersonic cooling air film, although the temperature of the wall surface of the single wall section is cooled to a temperature close to the total temperature of the air film inlet in a certain area away from the air film inlet at the downstream, the air film cooling capacity is rapidly attenuated with the mixing of the air film and the main flow, the cooling effect is correspondingly deteriorated, the temperature of the wall surface of the single wall section begins to rapidly rise, and the temperature of the wall surface of the single wall section is close to or exceeds the allowable temperature of the material in a shorter area. The heat flux density of the downstream of the extension section of the single-wall spray pipe is greatly reduced, the traditional mode of spraying the thermal barrier coating on the inner wall can only reduce the wall temperature by about 20K, the cooling effect is limited, in addition, the spraying process is complex, and the coating is easy to fall off under the complex force and thermal environment effect when the spray pipe works.
Disclosure of Invention
The technical solution of the invention is as follows: the defects of the prior art are overcome, the layered supersonic air film cooling single-wall spray pipe extension section is provided, and the coolant forms a layered air film through the inner and outer circles of supersonic air film holes, so that the highest wall surface temperature of the single-wall spray pipe extension section is effectively reduced.
The technical scheme of the invention is as follows:
a layered supersonic speed air film cooling single-wall spray pipe extension section comprises a supersonic speed air film spraying device and a single-wall spray pipe extension section;
the supersonic speed air film spraying device is of an annular structure, one end of the supersonic speed air film spraying device is welded with the upper section of the spray pipe, and the other end of the supersonic speed air film spraying device is welded with the extension section of the single-wall spray pipe; the outer side of the annular structure is provided with a hole, the hole is used as a coolant inlet, and after being welded in place, a closed annular cavity is formed between the annular structure and the upper section of the spray pipe, and the annular cavity is used as a coolant inlet collector; two circles of supersonic speed air film holes are arranged at one end, close to the extension section of the single-wall spray pipe, of the supersonic speed air film spraying device, and the supersonic speed air film holes are respectively an inner circle of supersonic speed air film holes and an outer circle of supersonic speed air film holes.
Preferably, the inner ring supersonic speed air film hole and the outer ring supersonic speed air film hole are both in flat structures.
Preferably, the inner ring supersonic gas film holes and the outer ring supersonic gas film holes are in a shrinkage-expansion mode along the flowing direction of the coolant, namely, each inner ring supersonic gas film hole and each outer ring supersonic gas film hole are sequentially provided with a shrinkage section, a straight section and an expansion section along the flowing direction of the coolant; the straight section is used for controlling and stabilizing the flow rate of the coolant, and the cross-sectional area of the straight section perpendicular to the flow direction is the throat area of the supersonic speed air film hole.
Preferably, the distribution of the coolant flow of the inner ring and the outer ring is realized by controlling the throat area ratio of the ultrasonic air film holes of the inner ring and the outer ring, wherein a part of coolant is sprayed out of the ultrasonic air film spraying device through a plurality of ultrasonic air film holes of the inner ring to form an inner ultrasonic air film; and the rest coolant is sprayed out of the supersonic air film spraying device through the outer ring supersonic air film holes to form an outer layer supersonic air film.
Preferably, the upper surface and the lower surface of the supersonic air film hole of the inner ring are parallel, the included angle between the tangent line of the side wall surface of the inlet and outlet of the contraction section and the flowing direction of the coolant is 0, and the two side wall surfaces are contracted smoothly; the two side wall surfaces of the expansion section are expanded by inclined planes, the inner ultrasonic air film is sprayed out at a certain angle at the outlet, the adjacent inner ultrasonic air films are rapidly intersected along the circumferential direction of the spray pipe to form a continuous air film, and the heat transfer between the main stream fuel gas and the outer ultrasonic air film is weakened.
Preferably, the upper surface and the lower surface of the contraction section of the outer ring supersonic speed air film hole are parallel, the included angle between the tangent line of the side wall surface of the inlet and the outlet of the contraction section and the flowing direction of the coolant is 0, and the two side wall surfaces are contracted smoothly; the two side wall surfaces of the expansion section are expanded, the included angle between the tangent line of the side wall surface of the inlet and the outlet of the expansion section and the flowing direction of the coolant is 0, and the upper surface and the lower surface of the expansion section are expanded.
Preferably, the maximum height of the expansion of the upper surface and the lower surface of the expansion section of the supersonic air film hole of the outer ring is 1.2-2.5 times of the height of the contraction section.
Preferably, the outer ring supersonic gas film holes and the inner ring supersonic gas film holes are staggered along the circumferential direction.
Compared with the prior art, the invention has the following beneficial effects:
(1) The invention provides a layered supersonic air film cooling scheme, which adopts a flat shrinkage-expansion hole, has a simple structure and a compact form, is suitable for arranging double-layer air film holes on a smaller height, and effectively reduces the highest wall surface temperature of an extension section of a single-wall spray pipe by forming a layered air film through inner and outer circles of supersonic air film holes by coolant.
(2) By applying the invention, the highest wall surface temperature (namely service temperature) of the extension section of the single-wall spray pipe can be effectively reduced, so that materials with lower heat-resistant temperature can be selected, and the material cost and manufacturing process difficulty of the extension section of the single-wall spray pipe are reduced.
(3) The layered supersonic air film cooling scheme of the invention obviously reduces the temperature of the highest wall surface of the extension section of the single-wall spray pipe, can avoid the use of complex processes such as high-emissivity coating, thermal barrier coating and the like, and has no risk caused by easy falling of the coating.
(4) The layered supersonic air film cooling scheme can prolong the acting length of the air film and can be applied to the extension section of the upper-stage engine jet pipe with larger area ratio (longer axial length).
(5) The layered supersonic air film cooling scheme can obviously reduce the service temperature of the extension section of the single-wall spray pipe, reduce the influence of the rapid decrease of the material along with the temperature increase at high temperature, and further improve the structural reliability.
Drawings
FIG. 1 is a three-dimensional cross-sectional view of a layered supersonic film cooling single-wall nozzle extension;
FIG. 2 is a plan cross-sectional view of a single-wall nozzle extension for layered supersonic film cooling;
fig. 3 is a structural form diagram of a supersonic air film spraying device, wherein (a) is an axial sectional view of an inner ring air film hole, (b) is a distribution diagram of the inner ring and the outer ring supersonic air film hole along the circumferential direction, (c) is an axial sectional view of the outer ring air film hole, (d) is a tangential sectional view of an inner ring single air film hole, and (e) is a tangential sectional view of an outer ring single air film hole;
FIG. 4 is a graph showing wall temperature comparisons for a single wall nozzle extension for prior art and inventive layered supersonic film cooling.
Detailed Description
According to the layered supersonic air film cooling single-wall spray pipe extension section designed by the invention, coolant forms a layered air film through the inner and outer circles of supersonic air film holes to thermally protect the single-wall spray pipe extension section, the inner air film is directly contacted with main flow gas, heat transfer between the outer air film and the main flow gas in the initial section is reduced, the outer air film is sprayed out of the air film holes at a higher speed, acts on the wall surface of the downstream single-wall spray pipe extension section, can effectively reduce the highest wall surface temperature of the single-wall spray pipe extension section or increase the length of the coolable single-wall spray pipe extension section, and can be applied to the field of aerospace propulsion.
The layered supersonic air film cooling spray pipe extension section comprises a supersonic air film spraying device 2 and a single-wall spray pipe extension section 3, wherein the parts are connected in a welding mode, as shown in figures 1-3. The supersonic speed air film spraying device 2 is of an annular structure, one end of the supersonic speed air film spraying device is welded with the upper section 1 of the spray pipe, and the other end of the supersonic speed air film spraying device is welded with the single-wall spray pipe extension section 3; the outer side of the annular structure is provided with a hole as a coolant inlet 21, and after being welded in place, a closed annular cavity is formed between the annular structure and the upper section 1 of the spray pipe, and the annular cavity is used as a coolant inlet collector 22; the coolant that cools the single wall nozzle extension 3 enters the coolant inlet header 22 from the coolant inlet 21. Two circles of supersonic speed air film holes are arranged at one end, close to the single-wall spray pipe extension section 3, of the supersonic speed air film spraying device 2, and the two circles of supersonic speed air film holes are respectively an inner circle of supersonic speed air film holes 23 and an outer circle of supersonic speed air film holes 24.
In order to realize that the double-layer air film hole is arranged on a smaller structural height, the supersonic air film hole adopts a flat structure and is in a contracted-expanded form along the flowing direction of the coolant, a small flat section is arranged between the contracted section and the expanded section and used for controlling and stabilizing the flow of the coolant, and the cross section area of the flat section perpendicular to the flowing direction is the throat area of the supersonic air film hole. The maximum section of the expansion section is the outlet of the air film hole. The distribution of the coolant flow of the inner ring and the outer ring can be realized by controlling the throat area ratio of the supersonic speed air film holes of the inner ring and the outer ring. The control of the air flow speed of the air film hole outlet can be realized by controlling the area ratio of the air film hole outlet to the air film hole throat, and the area ratio of the outer ring air film hole outlet to the throat is increased to improve the outer layer air film spraying speed.
In one embodiment, the throat area ratio of the supersonic speed air film holes of the inner ring and the outer ring is 3:7. Therefore, about 30% of the coolant is sprayed out of the supersonic air film spraying device 2 through a plurality of shrinkage-expansion supersonic air film holes of the inner ring to form an inner layer supersonic air film 4; and the rest about 70% of the coolant passes through a plurality of shrinkage-expansion supersonic air film holes on the outer ring and is sprayed out of the supersonic air film spraying device 2 to form an outer layer supersonic air film 5.
As shown in fig. 3 (a), the upper and lower surfaces of the inner ring supersonic gas film hole 23 are parallel. As shown in fig. 3 (d), the included angle between the tangent line of the side wall surface of the inlet and outlet of the contraction section and the flowing direction of the coolant is 0, the two side surfaces of the expansion section are smooth and contracted, the two side surfaces of the expansion section are expanded by inclined planes, the supersonic gas film is sprayed out from the outlet at a certain angle, and the adjacent gas films are rapidly intersected along the circumferential direction of the spray pipe to form a continuous gas film, so that the heat transfer between the main flow gas 0 and the outer supersonic gas film 5 is weakened.
As shown in fig. 3 (c), the upper and lower surfaces of the contracted section of the outer ring supersonic gas film hole 24 are parallel. The included angle between the tangent line of the side wall surface of the inlet and outlet of the contraction section and the flowing direction of the coolant is 0, and the two side wall surfaces are smoothly contracted; as shown in fig. 3 (e), the two side wall surfaces of the expansion section are expanded, the angle between the tangent line of the inlet and outlet side wall surfaces of the expansion section and the flowing direction of the coolant is 0, and the upper and lower surfaces of the expansion section are expanded. As shown in fig. 3 (c), the upper and lower surfaces of the expansion section are also expanded slightly, the maximum height of the upper and lower surfaces of the expansion section of the outer ring supersonic speed air film hole 24 is 1.2-2.5 times of the height of the contraction section, so that the larger area ratio of the air film hole outlet to the throat is realized, the ejection speed of the outer layer air film is improved, the ejection angle of the outer layer supersonic speed air film is 0, the speed loss generated by the intersection of adjacent air films is reduced, the air film reaches the downstream of the single-wall spray pipe extension section at a faster speed, and the downstream wall surface is cooled.
As shown in fig. 3 (b), the outer ring supersonic gas film holes 24 and the inner ring supersonic gas film holes 23 are staggered along the circumferential direction, so as to improve the structural reliability and avoid the too low structural strength caused by the fact that the inner ring and the outer ring are perforated at the same circumferential position. The inner circle and the outer circle of supersonic velocity air film holes are different in size, and the same circle of inner air film holes are the same in size. The distance between every two adjacent holes of the supersonic speed air film hole is 0.3-0.8 times of the width of the air film hole outlet; the distance between the inner and outer ring supersonic speed air film holes is 0.6-1.2 times of the height of the inner ring supersonic speed air film hole; the height of the inner ring supersonic speed air film hole from the inner side wall surface of the supersonic speed air film spraying device is 1.2-2.5mm.
The invention divides the coolant for cooling the extension section of the single-wall spray pipe into two parts, a small amount of coolant (about 30%) is sprayed out through the inner ring hole of the supersonic speed air film spraying device to form an inner layer air film, the inner layer air film is directly contacted with main stream fuel gas, and the rest of coolant is sprayed out through the outer ring hole of the supersonic speed air film spraying device at a higher speed than the inner layer air film to form an outer layer air film. The inner air film weakens the heat transfer between the main stream fuel gas and the outer air film, and the outer air film is sprayed out at a higher speed, so that the coolant with lower temperature is brought to the downstream of the extension section of the single-wall spray pipe, and the temperature of the downstream wall surface is reduced.
The expansion of the coolant is accelerated when the expansion part of the air film hole flows, the static pressure is gradually reduced, the speed is correspondingly increased, the inner air film is directly contacted with the main stream gas, in order to avoid complex shock wave-expansion wave system generated by larger static pressure difference of the contact area and the inner air film hole, the inner air film hole adopts the design principle of static pressure matching, namely the area ratio of the air film hole outlet to the air film hole throat depends on the local main stream gas static pressure of the air film hole outlet, and the speed when the coolant is sprayed out of the air film hole is correspondingly determined. The outer layer air film is larger than the inner ring air film hole in area ratio of the air film hole outlet to the air film hole throat in order to obtain higher ejection speed.
Therefore, the design method of the supersonic velocity air film spraying device comprises the following steps:
(1) According to the distribution of the coolant flow of the inner ring and the outer ring, designing the throat area ratio of the inner ring supersonic speed air film hole to the outer ring supersonic speed air film hole;
(2) Designing the area ratio of the inner ring supersonic speed air film hole outlet to the throat part of the inner ring supersonic speed air film hole according to the local main flow gas static pressure of the inner ring supersonic speed air film hole outlet;
(3) The area ratio of the outlet of the outer ring supersonic speed air film hole to the throat part of the outer ring supersonic speed air film hole is larger than the ratio of the inner ring so as to obtain higher ejection speed;
(4) And designing the supersonic speed air film spraying device according to the structure and the area ratio.
Through simulation calculation, under the condition that the coolant flow and inlet parameters, the length of the extension section of the single-wall spray pipe and the emissivity of the single-wall section material are kept unchanged, the highest wall surface temperature of the extension section of the single-wall spray pipe can be reduced by about 100K by using the method disclosed by the invention, as shown in figure 4. Compared with the existing supersonic speed air film cooling scheme, the method can obviously reduce the highest wall temperature and improve the structural reliability.
Although the present invention has been described in terms of the preferred embodiments, it is not intended to be limited to the embodiments, and any person skilled in the art can make any possible variations and modifications to the technical solution of the present invention by using the methods and technical matters disclosed above without departing from the spirit and scope of the present invention, so any simple modifications, equivalent variations and modifications to the embodiments described above according to the technical matters of the present invention are within the scope of the technical matters of the present invention.
Claims (8)
1. A layered supersonic speed air film cooling single-wall spray pipe extension section is characterized in that: comprises a supersonic speed air film spraying device (2) and a single-wall spray pipe extension section (3);
the supersonic air film spraying device (2) is of an annular structure, one end of the supersonic air film spraying device is welded with the upper section (1) of the spray pipe, and the other end of the supersonic air film spraying device is welded with the single-wall spray pipe extension section (3); the outer side of the annular structure is provided with a hole as a coolant inlet (21), and after being welded in place, a closed annular cavity is formed between the annular structure and the upper section (1) of the spray pipe, and the annular cavity is used as a coolant inlet collector 22; two circles of supersonic speed air film holes are arranged at one end, close to the single-wall spray pipe extension section (3), of the supersonic speed air film spraying device (2), and the two circles of supersonic speed air film holes are respectively an inner circle of supersonic speed air film holes (23) and an outer circle of supersonic speed air film holes (24).
2. The layered supersonic film cooled single wall nozzle extension of claim 1, wherein: the inner ring supersonic speed air film hole (23) and the outer ring supersonic speed air film hole (24) are both in flat structures.
3. The layered supersonic film cooled single wall nozzle extension of claim 2, wherein: the inner ring supersonic speed air film holes (23) and the outer ring supersonic speed air film holes (24) are in a shrinkage-expansion mode along the flowing direction of the coolant, namely, each inner ring supersonic speed air film hole (23) and each outer ring supersonic speed air film hole (24) are sequentially provided with a shrinkage section, a straight section and an expansion section along the flowing direction of the coolant; the straight section is used for controlling and stabilizing the flow rate of the coolant, and the cross-sectional area of the straight section perpendicular to the flow direction is the throat area of the supersonic speed air film hole.
4. A layered supersonic film cooled single wall nozzle extension according to claim 3, wherein: the distribution of the coolant flow of the inner ring and the outer ring is realized by controlling the throat area ratio of the supersonic gas film holes of the inner ring and the outer ring, wherein a part of coolant is sprayed out of the supersonic gas film spraying device (2) through a plurality of supersonic gas film holes of the inner ring to form an inner supersonic gas film (4); and the rest coolant is sprayed out of the supersonic air film spraying device (2) through the outer ring supersonic air film holes to form an outer layer supersonic air film (5).
5. The layered supersonic film cooled single wall nozzle extension of claim 4, wherein: the upper surface and the lower surface of the inner ring supersonic speed air film hole (23) are parallel, the included angle between the tangent line of the side wall surface of the inlet and outlet of the contraction section and the flowing direction of the coolant is 0, and the two side wall surfaces are contracted smoothly; the two side wall surfaces of the expansion section are expanded by inclined planes, the inner ultrasonic air film (4) is sprayed out at a certain angle at the outlet, the adjacent inner ultrasonic air films are rapidly intersected along the circumferential direction of the spray pipe to form a continuous air film, and the heat transfer between main stream fuel gas and the outer ultrasonic air film (5) is weakened.
6. The layered supersonic film cooled single wall nozzle extension of claim 4, wherein: the upper surface and the lower surface of a contraction section of the outer ring supersonic speed air film hole (24) are parallel, the included angle between the tangent line of the side wall surface of an inlet and an outlet of the contraction section and the flowing direction of the coolant is 0, and the two side wall surfaces are contracted smoothly; the two side wall surfaces of the expansion section are expanded, the included angle between the tangent line of the side wall surface of the inlet and the outlet of the expansion section and the flowing direction of the coolant is 0, and the upper surface and the lower surface of the expansion section are expanded.
7. The layered supersonic film cooled single wall nozzle extension of claim 6, wherein: the maximum height of the expansion of the upper part and the lower part of the expansion section of the outer ring supersonic speed air film hole (24) is 1.2-2.5 times of the height of the contraction section.
8. The layered supersonic film cooled single wall nozzle extension of claim 2, wherein: the outer ring supersonic air film holes (24) and the inner ring supersonic air film holes (23) are staggered along the circumferential direction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311026501.2A CN117090709A (en) | 2023-08-15 | 2023-08-15 | Layered supersonic air film cooling single-wall spray pipe extension section |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311026501.2A CN117090709A (en) | 2023-08-15 | 2023-08-15 | Layered supersonic air film cooling single-wall spray pipe extension section |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117090709A true CN117090709A (en) | 2023-11-21 |
Family
ID=88773014
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311026501.2A Pending CN117090709A (en) | 2023-08-15 | 2023-08-15 | Layered supersonic air film cooling single-wall spray pipe extension section |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117090709A (en) |
-
2023
- 2023-08-15 CN CN202311026501.2A patent/CN117090709A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US4565490A (en) | Integrated gas/steam nozzle | |
| EP2865981B1 (en) | Counter-flow heat exchange systems | |
| EP0815995B1 (en) | Method for making cylindrical structures with cooling channels | |
| US11248491B2 (en) | Additively deposited gas turbine engine cooling component | |
| US10914177B2 (en) | Dual-walled components for a gas turbine engine | |
| US7347041B1 (en) | Rocket engine combustion chamber | |
| US4543781A (en) | Annular combustor for gas turbine | |
| US4545197A (en) | Process for directing a combustion gas stream onto rotatable blades of a gas turbine | |
| US11199097B2 (en) | Air-film cooled component for a gas turbine engine | |
| CN109269756B (en) | A kind of water-cooled jet pipe | |
| Smith et al. | Cold spray direct fabrication-high rate, solid state, material consolidation | |
| US4638628A (en) | Process for directing a combustion gas stream onto rotatable blades of a gas turbine | |
| CN117090709A (en) | Layered supersonic air film cooling single-wall spray pipe extension section | |
| CN113217949A (en) | Combustion chamber diverging and cooling structure and ramjet combustion chamber | |
| Bunker | Innovative gas turbine cooling techniques | |
| Dannhauer | Investigation of trailing edge cooling concepts in a high pressure turbine cascade: Analysis of the adiabatic film cooling effectiveness | |
| CN111927644B (en) | Cooling heat protection device for high-temperature wall surface | |
| Sato et al. | Development study of the precooler of the ATREX engine | |
| US20210156339A1 (en) | Cooling system for an engine assembly | |
| CN115949532A (en) | Extension section of graded pre-cooling single-wall spray pipe | |
| Takegoshi et al. | Firing-tests of a rocket combustor for combined cycle engine at various conditions | |
| JPH06330816A (en) | High temperature combustion engine | |
| CN116517722A (en) | Binary receiving and expanding spray pipe with composite air film cooling structure | |
| JP2006513362A (en) | Multi-nozzle grid missile propulsion system | |
| CN111927647A (en) | Cooling heat protection device for high-temperature head cone |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |