CN115949532A - Extension section of graded pre-cooling single-wall spray pipe - Google Patents
Extension section of graded pre-cooling single-wall spray pipe Download PDFInfo
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- CN115949532A CN115949532A CN202211457301.8A CN202211457301A CN115949532A CN 115949532 A CN115949532 A CN 115949532A CN 202211457301 A CN202211457301 A CN 202211457301A CN 115949532 A CN115949532 A CN 115949532A
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
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Abstract
The invention relates to a graded pre-cooling single-wall spray pipe extension section which comprises an upper section of the single-wall spray pipe extension section and a lower section of the single-wall spray pipe extension section, wherein turbine waste gas is divided into two parts according to a proportion, no more than 30% of the turbine waste gas forms a first-stage supersonic speed gas film, a protective layer with a lower temperature is formed in an area close to the inner wall surface of a single-wall upper section matrix to separate main flow gas with a higher temperature from the single-wall upper section matrix, and a second-stage supersonic speed gas film is arranged at a position where the cooling efficiency of the first-stage gas film is reduced to 80% or the highest wall surface temperature of the single-wall spray pipe extension section is close to the allowable material temperature to thermally protect the inner wall of the residual matrix of the single-wall section. The invention can obviously reduce the highest temperature of the wall surface of the structure under specific flow distribution.
Description
Technical Field
The invention relates to a graded pre-cooling single-wall spray pipe extension section, and belongs to the technical field of liquid rocket engines.
Background
The gas generator circulating liquid rocket engine usually introduces turbine exhaust gas into the nozzle extension section in the form of supersonic speed gas film, and combines radiation cooling to cool the lower section of the nozzle to form a single-wall nozzle extension section. However, for higher stage engines with larger nozzle exit area ratios, a single stage supersonic cooling film may not be able to achieve cooling of a single wall section of nozzle extension of sufficient length due to the longer axial length of the nozzle extension, which is limited by the allowable material temperature.
Considering that the single-stage supersonic cooling gas film can cool the wall temperature of the single-stage wall section to a temperature close to the total temperature of the gas film inlet in a certain area of the gas film inlet, the temperature of the single-stage wall section is far lower than the allowable temperature of the material, but then the wall temperature of the single-stage wall section begins to rise rapidly, namely the position close to the supersonic gas film inlet section wastes cooling capacity due to large cooling flow and over-sufficient cooling effect, and the heat resistance of the material and the cooling capacity of turbine waste gas (coolant) can be fully utilized through certain cooling flow distribution.
The heat flux density of the downstream wall surface of the throat part of the liquid rocket engine is gradually reduced, the heat protection requirement is correspondingly weakened, in order to reduce the structural weight, a sectional structure is adopted in a large area compared with the upper-level engine spray pipe, the extension section of the spray pipe is of a single-layer thin-wall structure cooled by combining radiation and an ultrasonic air film, common materials 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 ℃, the niobium-tungsten alloy and the composite material are high in cost, and the forming process of the composite material with the diameter of more than 1.5m is immature, so that the domestic single-wall spray pipe is often made of the nickel-based alloy such as GH 3230. For the gas generator circulating liquid rocket engine supersonic speed gas film usually comes from turbine exhaust gas, the existing structure form at home and abroad is to introduce turbine exhaust gas at about 500 ℃ into a single-wall spray pipe through a single large collector, and the turbine exhaust gas forms supersonic speed wall flow through a circular seam type or discrete hole type contraction-expansion type spraying structure to carry out thermal protection on the wall surface of the downstream single-wall spray pipe. However, with the blending of the single-stage film with the main stream, the film cooling capacity is rapidly reduced, and the cooling effect is correspondingly deteriorated.
Disclosure of Invention
The technical problem solved by the invention is as follows: the defects in the prior art are overcome, and the extension section of the graded pre-cooling single-wall spray pipe is provided, so that the highest temperature of the wall surface of the structure is obviously reduced under specific flow distribution.
The technical scheme of the invention is as follows:
a graded pre-cooling single-wall spray pipe extension section comprises an upper section of the single-wall spray pipe extension section and a lower section of the single-wall spray pipe extension section,
the tail end of the outer wall of the single-wall spray pipe is provided with an upper section of an extension section of the single-wall spray pipe, the upper section of the extension section of the single-wall spray pipe comprises a primary air film inlet, a primary air film collector, a primary air film flow equalizing plate, a primary air film contraction-expansion annular seam and a single-wall upper section substrate,
the upper base body of the single wall is connected with the outer wall of the single wall spray pipe in a clearance way, a first-level air film inlet, a first-level air film collector, a first-level air film flow equalizing plate and a first-level air film contraction-expansion circular seam are sequentially arranged at the clearance,
the tail end of the outer wall of the upper section of the single-wall spray pipe extension section is provided with a lower section of the single-wall spray pipe extension section, the lower section of the single-wall spray pipe extension section comprises a secondary air film inlet, a secondary air film collector, a secondary air film flow equalizing plate, a secondary air film contraction-expansion annular seam and a single-wall lower section matrix,
the lower base body of the single wall is connected with the outer wall of the upper section of the extension section of the single wall spray pipe in a clearance way, a secondary air film inlet, a secondary air film collector, a secondary air film flow equalizing plate and a secondary air film contraction-expansion circular seam are sequentially arranged at the clearance,
the turbine waste gas is divided into two parts according to the proportion, wherein no more than 30% of the turbine waste gas forms a first-stage supersonic speed gas film, a protective layer with lower temperature is formed in an area close to the inner wall surface of the single-wall upper section matrix to separate main flow gas with higher temperature from the single-wall upper section matrix, and a second-stage supersonic speed gas film is arranged at a position where the cooling efficiency of the first-stage gas film is reduced to 80% or the highest wall surface temperature of the upper section of the single-wall nozzle extension section is close to the allowable material temperature, so that the inner wall of the residual matrix of the single-wall section is subjected to thermal protection.
Further, the first-stage gas film contraction-expansion circular seam is smaller than the second-stage gas film contraction-expansion circular seam.
Furthermore, the first-stage gas film contraction-expansion circular seam and the second-stage gas film contraction-expansion circular seam are both conical throats, and the size of the circular seam is determined based on cooling flow.
Furthermore, a plurality of holes are uniformly distributed on the first-stage gas film flow equalizing plate, and the number and the size of the holes are designed based on local flow velocity.
Furthermore, the primary air film collector is buckled on the outer wall of the single-wall spray pipe in a semicircular shape, and a flow equalizing cavity is formed at the inlet of the primary air film.
Furthermore, a plurality of holes are uniformly distributed on the first-stage gas film flow equalizing plate, so that the turbine exhaust gas entering the first-stage gas film collector through the first-stage gas film inlet can uniformly enter the first-stage gas film contraction-expansion circular seam along the circumferential direction.
Furthermore, the turbine exhaust gas is expanded and accelerated by the contraction-expansion circular seam to form a first-stage supersonic air film, the supersonic air film at a lower temperature flows tightly attached to the inner wall of the single-wall upper-section matrix to separate the single-wall upper-section matrix from the main stream gas at a higher temperature, and cooling is realized.
Furthermore, the secondary air film collector is buckled on the outer wall of the upper section of the extension section of the single-wall spray pipe in a semicircular shape, and a flow equalizing cavity is formed at the inlet of the secondary air film.
Furthermore, a plurality of holes are uniformly distributed on the secondary air film flow equalizing plate, so that the turbine exhaust gas entering the secondary air film collector through the secondary air film inlet uniformly enters the secondary air film contraction-expansion circular seam along the circumferential direction.
Furthermore, the secondary gas film shrinks and expands the annular seam to accelerate the expansion of the turbine exhaust gas and form a secondary supersonic gas film, the secondary supersonic gas film with lower temperature flows tightly attached to the inner wall of the single-wall lower-section matrix, and the single-wall lower-section matrix is separated from the main stream gas with higher temperature to realize cooling.
Compared with the prior art, the invention has the beneficial effects that:
(1) Compared with a single-stage supersonic air film cooling scheme, the single-stage supersonic air film cooling method can effectively prolong the total effective air film length, can be applied to the engine spray pipe extension section with a larger area ratio, and can reduce the highest wall surface temperature of the single-wall section by more than 140K under the condition of keeping the total flow of the turbine exhaust gas, the inlet parameters, the single-wall section spray pipe length and the single-wall section material radiation emissivity unchanged, and the reduction amplitude reaches 10%;
(2) The grading pre-cooling scheme of the invention obviously reduces the highest wall surface temperature of a single wall section through certain cooling flow distribution, and can avoid the use of complex processes such as high-radiation emissivity coatings, thermal barrier coatings and the like.
Drawings
FIG. 1 is a schematic view of a staged pre-cooling single wall nozzle extension;
FIG. 2 is a single wall nozzle extension configuration;
FIG. 3 is a structural form diagram of an upper section of a single-wall nozzle extension;
FIG. 4 is a view of the lower section of a single wall nozzle extension;
FIG. 5 is a wall temperature contrast plot of a single wall section of a prior art single stage and a staged supersonic air film cooling single wall section of the present invention.
Detailed Description
The invention is further illustrated by the following examples.
A graded pre-cooling single-wall nozzle extension, as shown in figures 1-4, comprises a single-wall nozzle extension upper section 2 and a single-wall nozzle extension lower section 4,
the tail end of the outer wall of the single-wall spray pipe is provided with an extension section upper section 2 of the single-wall spray pipe, the extension section upper section 2 of the single-wall spray pipe comprises a primary air film inlet 21, a primary air film collector 22, a primary air film flow equalizing plate 23, a primary air film contraction-expansion annular seam 24 and a single-wall upper section substrate 25,
the single-wall upper segment base body 25 is connected on the outer wall of the single-wall spray pipe in a clearance way, a first-level air film inlet 21, a first-level air film collector 22, a first-level air film flow equalizing plate 23 and a first-level air film contraction-expansion circular seam 24 are sequentially arranged at the clearance,
the tail end of the outer wall of the upper section 2 of the single-wall spray pipe extension section is provided with a lower section 4 of the single-wall spray pipe extension section, the lower section 4 of the single-wall spray pipe extension section comprises a secondary air film inlet 41, a secondary air film collector 42, a secondary air film flow equalizing plate 43, a secondary air film contraction-expansion annular seam 44 and a single-wall lower section matrix 45,
the single-wall lower base 45 is connected with the outer wall of the single-wall nozzle extension section 2 in a clearance way, a secondary air film inlet 41, a secondary air film collector 42, a secondary air film flow equalizing plate 43 and a secondary air film contraction-expansion annular seam 44 are sequentially arranged at the clearance,
the turbine exhaust gas is divided into two parts according to the proportion, wherein no more than 30% of the turbine exhaust gas forms a first-stage supersonic speed gas film 3, a protective layer with lower temperature is formed in an area close to the inner wall surface of the single-wall upper-section base body 25 to separate main flow gas with higher temperature from the single-wall upper-section base body 25, and a second-stage supersonic speed gas film 5 is arranged at a position where the cooling efficiency of the first-stage gas film is reduced to 80% or the highest wall surface temperature of the upper section 2 of the single-wall spray pipe extension section is close to the allowable material temperature, so that the inner wall of the residual base body of the single-wall section is subjected to thermal protection.
The first-stage gas film contraction-expansion circular seam 24 and the second-stage gas film contraction-expansion circular seam 44 are both conical throats, and the size of the circular seams is determined based on cooling flow. The primary gas film constricting-expanding circumferential seam 24 is smaller than the secondary gas film constricting-expanding circumferential seam 44.
The first-stage gas film flow equalizing plate 23 is uniformly distributed with a plurality of holes, the number and the size of the holes are designed based on local flow velocity, and the first-stage gas film flow equalizing plate 23 is uniformly distributed with a plurality of holes, so that the turbine exhaust gas entering the first-stage gas film collector 22 through the first-stage gas film inlet 21 uniformly enters the first-stage gas film contraction-expansion annular seam 24 along the circumferential direction.
The primary air film collector 22 is buckled on the outer wall of the single-wall spray pipe in a semicircular shape, and a flow equalizing cavity is formed at the primary air film inlet 21. The secondary air film collector 42 is buckled on the outer wall of the upper section 2 of the extension section of the single-wall spray pipe in a semicircular shape, and a flow equalizing cavity is formed at the secondary air film inlet 41.
The contraction-expansion circular seam 24 leads the turbine waste gas to expand and accelerate to form a first-stage supersonic speed gas film 3, the supersonic speed gas film 3 with lower temperature flows tightly attached to the inner wall of the single-wall upper-section matrix 25, and the single-wall upper-section matrix 25 and the higher-wall upper-section matrix 25 are connected with each other
A plurality of holes are uniformly distributed on the secondary air film flow equalizing plate 43, so that the turbine exhaust gas entering the secondary air film collector 42 through the secondary air film inlet 41 uniformly enters the secondary air film contraction-expansion annular seam 44 along the circumferential direction.
The secondary gas film contraction-expansion annular seam 44 enables the turbine exhaust gas to expand and accelerate to form a secondary supersonic speed gas film 5, the secondary supersonic speed gas film 5 with a lower temperature flows to be tightly attached to the inner wall of the single-wall lower-section matrix 45, and the single-wall lower-section matrix 45 is separated from the main flow gas 0 with a higher temperature to realize cooling.
The existing single-stage supersonic gas film cooling method is characterized in that all turbine exhaust gas is introduced into a spray pipe extension section through a single contraction-expansion circular seam to form supersonic wall flow, the supersonic gas film is mixed with main stream fuel gas along the axial direction of the spray pipe, the cooling capacity of the supersonic gas film is rapidly weakened after a certain distance, and the wall temperature of a single-wall section is rapidly increased. In a longer section of area near the gas film outlet, the temperature of the wall surface of the single-wall section is basically equal to the temperature of the turbine exhaust gas at the gas film inlet and is far lower than the allowable temperature of the material of the single-wall nozzle, and the temperature of the rear wall surface is quickly increased.
The core thought of this patent is through distributing cooling flow (turbine waste gas), and the wall temperature that closes on the gas film export section with single wall spray tube improves, makes its highest temperature slightly less than the temperature of material can, saves more many parts cooling flow and regards as the second grade gas film, carries out thermal protection to the longer region of single wall hypomere. The highest wall temperature of the downstream of the first-stage gas film and the second-stage gas film is basically equivalent and is lower than the allowable temperature of the material, so that the aims of fully utilizing the heat resistance of the material and the cooling capacity of the turbine exhaust gas are fulfilled.
The invention uses a small amount (about 30%) of turbine waste gas to form a primary supersonic air film, forms a protective layer with lower temperature in the area close to the inner wall surface of the single-wall section matrix to separate the main stream gas with higher temperature from the single-wall section matrix, and introduces a secondary supersonic air film at the position where the cooling efficiency of the primary air film is reduced to about 80% or the temperature of the wall surface of the single-wall section is close to the allowable temperature of the material to carry out thermal protection on the inner wall of the residual matrix of the single-wall section.
Compared with a single-stage supersonic air film cooling scheme, the single-stage supersonic air film cooling method can effectively prolong the total effective air film length, can be applied to the engine spray pipe extension section with a larger area ratio, and can reduce the highest wall surface temperature of the single-wall section by over 140K to 10% under the condition of keeping the total flow of the turbine exhaust gas, the inlet parameters, the single-wall section spray pipe length and the single-wall section material radiation emissivity unchanged, as shown in FIG. 5.
The grading pre-cooling scheme of the invention obviously reduces the highest wall surface temperature of a single wall section through certain cooling flow distribution, and can avoid the use of complex processes such as high-radiation emissivity coatings, thermal barrier coatings and the like.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Claims (10)
1. A graded pre-cooling single-wall spray pipe extension section is characterized by comprising an upper section (2) of the single-wall spray pipe extension section and a lower section (4) of the single-wall spray pipe extension section,
the tail end of the outer wall of the single-wall spray pipe is provided with an extension section upper section (2) of the single-wall spray pipe, the extension section upper section (2) of the single-wall spray pipe comprises a primary air film inlet (21), a primary air film collector (22), a primary air film flow equalizing plate (23), a primary air film contraction-expansion circumferential seam (24) and a single-wall upper section base body (25),
the single-wall upper section matrix (25) is connected on the outer wall of the single-wall spray pipe in a clearance way, a first-level air film inlet (21), a first-level air film collector (22), a first-level air film flow equalizing plate (23) and a first-level air film contraction-expansion circular seam (24) are sequentially arranged at the clearance,
the tail end of the outer wall of the single-wall spray pipe extension section upper section (2) is provided with a single-wall spray pipe extension section lower section (4), the single-wall spray pipe extension section lower section (4) comprises a secondary air film inlet (41), a secondary air film collector (42), a secondary air film flow equalizing plate (43), a secondary air film contraction-expansion circular seam (44) and a single-wall lower section matrix (45),
the single-wall lower base body (45) is connected with the outer wall of the single-wall spray pipe extension section (2) in a clearance way, a secondary air film inlet (41), a secondary air film collector (42), a secondary air film flow equalizing plate (43) and a secondary air film contraction-expansion circular seam (44) are sequentially arranged at the clearance,
the turbine exhaust gas is divided into two parts according to the proportion, no more than 30% of the turbine exhaust gas forms a first-level supersonic speed gas film (3), a protective layer with lower temperature is formed in an area close to the inner wall surface of a single-wall upper section matrix (25) to separate main flow gas with higher temperature from the single-wall upper section matrix (25), a second-level supersonic speed gas film (5) is arranged at a position where the cooling efficiency of the first-level gas film is reduced to 80% or the highest wall surface temperature of an upper section (2) of a single-wall nozzle extension section is close to the allowable material temperature, and the inner wall of the residual matrix of the single-wall section is subjected to thermal protection.
2. A staged pre-cooling single-wall nozzle extension according to claim 1, wherein the primary gas film pinch-and-expand circumferential seam (24) is smaller than the secondary gas film pinch-and-expand circumferential seam (44).
3. A staged pre-cooling single-wall nozzle extension according to claim 1, wherein the conical throats are provided at the primary air film contraction-expansion circumferential seam (24) and at the secondary air film contraction-expansion circumferential seam (44), and the size of the circumferential seams is determined based on the cooling flow.
4. The staged pre-cooling single-wall nozzle extension according to claim 1, wherein a plurality of holes are uniformly distributed on the primary gas film flow equalizing plate (23), and the number and size of the holes are designed based on local flow velocity.
5. A staged pre-cooling single-wall nozzle extension according to claim 1, wherein the primary air film collector (22) is semi-circularly fastened to the outer wall of the single-wall nozzle, forming a flow equalizing cavity at the primary air film inlet (21).
6. The staged pre-cooling single-wall nozzle extension according to claim 1, wherein a plurality of holes are uniformly distributed on the primary gas film flow equalizing plate (23) so that the turbine exhaust gas entering the primary gas film collector (22) through the primary gas film inlet (21) uniformly enters the primary gas film contraction-expansion annular gap (24) along the circumferential direction.
7. The staged pre-cooling single-wall nozzle extension segment as claimed in claim 1, wherein the contraction-expansion annular seam (24) accelerates the expansion of the turbine exhaust gas to form a first-stage supersonic gas film (3), and the supersonic gas film (3) with a lower temperature flows to cling to the inner wall of the single-wall upper-section matrix (25) to separate the single-wall upper-section matrix (25) from the main flow gas (0) with a higher temperature, so as to realize cooling.
8. The staged pre-cooling single-wall lance extension according to claim 1, wherein the secondary gas film collector (42) is fastened to the outer wall of the single-wall lance extension upper section (2) in a semicircular shape, and a flow equalizing cavity is formed at the secondary gas film inlet (41).
9. A staged pre-cooling single-wall nozzle extension according to claim 1, wherein a plurality of holes are uniformly distributed on the secondary air film flow equalizing plate (43) so that the turbine exhaust gas entering the secondary air film collector (42) through the secondary air film inlet (41) can uniformly enter the secondary air film contraction-expansion annular seam (44) along the circumferential direction.
10. The staged pre-cooling single-wall nozzle extension segment as claimed in claim 1, wherein the secondary gas film contraction-expansion annular seam (44) accelerates the expansion of turbine exhaust gas to form a secondary supersonic gas film (5), the secondary supersonic gas film (5) with a lower temperature flows tightly against the inner wall of the single-wall lower-section matrix (45), and the single-wall lower-section matrix (45) is separated from the main flow gas (0) with a higher temperature to realize cooling.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211457301.8A CN115949532A (en) | 2022-11-21 | 2022-11-21 | Extension section of graded pre-cooling single-wall spray pipe |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202211457301.8A CN115949532A (en) | 2022-11-21 | 2022-11-21 | Extension section of graded pre-cooling single-wall spray pipe |
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| CN115949532A true CN115949532A (en) | 2023-04-11 |
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| CN202211457301.8A Pending CN115949532A (en) | 2022-11-21 | 2022-11-21 | Extension section of graded pre-cooling single-wall spray pipe |
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