CN112196632A - Prepressing turbine inlet shell and machining method thereof - Google Patents
Prepressing turbine inlet shell and machining method thereof Download PDFInfo
- Publication number
- CN112196632A CN112196632A CN202011011616.0A CN202011011616A CN112196632A CN 112196632 A CN112196632 A CN 112196632A CN 202011011616 A CN202011011616 A CN 202011011616A CN 112196632 A CN112196632 A CN 112196632A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K9/00—Arc welding or cutting
- B23K9/16—Arc welding or cutting making use of shielding gas
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
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- 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
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/46—Feeding propellants using pumps
Abstract
The invention provides a pre-pressed turbine inlet shell and a processing method thereof, and aims to solve the problem that the pre-pressed turbine shell for the existing rocket engine cannot be welded with high reliability. The prepressing turbine inlet shell comprises a shell body, a flange, a collector, a baffle and an inlet pipe, wherein the shell body is of a circular sleeve structure, and the flange is arranged below the shell body and is coaxial with the shell body; the collector comprises a first connecting section and a second connecting section, the cross sections of the first connecting section and the second connecting section are semi-annular, the first connecting section is fixedly arranged on the outer wall of the shell body and is buckled with the second connecting section to form an arc-shaped circular tube; the inlet of the arc-shaped circular tube is tangentially arranged along the shell body and is communicated with the outlet of the inlet tube, and the outlet is sealed by a baffle; the connecting part of the first connecting section and the shell body is provided with a plurality of supersonic nozzles, the inlets of the supersonic nozzles are communicated with the inner cavity of the collector, the outlets of the supersonic nozzles are communicated with the inner cavity of the shell body, and the center lines of the supersonic nozzles and the end surface of the flange are obliquely arranged.
Description
Technical Field
The invention belongs to the field of turbopumps of liquid rocket engines, and particularly relates to a prepressing turbine inlet shell and a processing method thereof.
Background
The turbo pump for the new generation liquid rocket engine generally adopts a pre-prepressing pump to carry out a pre-pressurization technology, the prepressing pump obtains driving force through a prepressing turbine, and driving media are generally high-pressure propellant, high-pressure gas or gas after a generator behind a main pump, so that the turbo pump has the characteristics of high temperature and high pressure. The existing pre-pressing turbine stator generally adopts a nozzle structure, and when the number of nozzles is more than 2, a collector welding structure is adopted for a front opening channel of the nozzle.
In order to improve the performance of the pre-compression turbine and reduce the backflow loss in front of the nozzle, the inlet of the collector is designed to be a tangential inlet, so that the reverse (medium flowing direction and nozzle direction) backflow and impact loss generated by a radial inlet are avoided. The inlet pipe is arranged at one side of the inlet direction of the nozzle and is respectively welded with the collector and the shell. The inlet pipe and the shell side welding seam can not realize groove welding due to the limitation of the shell outer wall surface space, and fillet welding is needed to be carried out after a shell is partially notched in order to ensure the welding space. However, due to the structural space limitation, the welding gun inclination angle is large during the above fillet welding, so that the manufacturability is poor, and the weld strength and reliability can not be ensured during the work under high working condition. Furthermore, for small sized precompression pump structures, fillet welding cannot be achieved.
Disclosure of Invention
The invention aims to solve the problem that the conventional prepressing turbine shell for a rocket engine cannot realize high-reliability welding, and provides a prepressing turbine inlet shell with good processing manufacturability and high reliability and a processing method thereof.
In order to realize the purpose, the technical scheme of the invention is as follows:
a pre-pressing turbine inlet shell comprises a shell body, a flange, a collector, a baffle and an inlet pipe, wherein the shell body is of a circular sleeve structure, and the flange is arranged below the shell body and is coaxial with the shell body; the collector comprises a first connecting section and a second connecting section, the cross sections of the first connecting section and the second connecting section are semi-annular, the first connecting section is fixedly arranged on the outer wall of the shell body and is buckled with the second connecting section to form an arc-shaped circular tube; the inlet of the arc-shaped circular tube is tangentially arranged along the shell body and is communicated with the outlet of the inlet tube, and the outlet is sealed by a baffle; a plurality of supersonic nozzles are arranged at the joint of the first connecting section and the shell body, the inlets of the supersonic nozzles are communicated with the inner cavity of the collector, the outlets of the supersonic nozzles are communicated with the inner cavity of the shell body, and the center lines of the supersonic nozzles and the end surface of the flange are obliquely arranged; a first Y-shaped outward groove is formed in the side wall of the first connecting section, and a first Y-shaped inward groove is formed in the end wall of the first connecting section; a third Y-shaped outward groove is formed in the side wall of the second connecting section, and a second Y-shaped outward groove is formed in the end wall of the second connecting section; a second Y-shaped inward groove matched with the first Y-shaped inward groove and a fourth Y-shaped outward groove matched with the second Y-shaped outward groove are formed in the pipe wall of the outlet end face of the inlet pipe; the first connecting section and the second connecting section are welded through a first Y-shaped inward groove and a third Y-shaped outward groove; one end of the first connecting section is welded with the inlet pipe through a first Y-shaped outward groove and a second Y-shaped inward groove, and the other end of the first connecting section is connected with the baffle through a fillet weld; one end of the second connecting section is welded with the inlet pipe through a second Y-shaped outward groove and a fourth Y-shaped outward groove, and the other end of the second connecting section is connected with the baffle through a fillet weld; the shell body and the flange are connected into a whole through electron beam welding, and positioning grooves are formed in the cylindrical surfaces of electron beam welding seams of the shell body and the flange.
Further, the minimum distance e between the electron beam welding seam position of the shell body and the flange and the intersection point of the supersonic nozzle outlet extension line and the inner cavity surface of the shell body is larger than 0.5 mm.
Furthermore, the boundary angle of the first Y-shaped outward bevel is 80-90 °, β is 110-130 °, the wrap angle of the second Y-shaped inward bevel is α + β, and the wrap angle of the fourth Y-shaped outward bevel is γ 360 ° - α - β.
Furthermore, the locating slot comprises a shell body half slot and a flange half slot which are matched, and the depth and the width of the shell body half slot and the flange half slot are both 0.5 mm-0.7 mm.
Meanwhile, the invention also provides a processing method of the inlet shell of the pre-pressing turbine, which comprises the following steps:
step one, processing a first connecting section on the outer cylindrical surface of a shell body, and processing a supersonic nozzle at the joint of the first connecting section and the shell body;
step two, processing a first Y-shaped outward groove on the side pipe wall of the first connecting section, and processing a first Y-shaped inward groove on the end pipe wall; processing a third Y-shaped outward groove on the side pipe wall of the second connecting section, and processing a second Y-shaped outward groove on the end pipe wall; processing a second Y-shaped inward groove and a fourth Y-shaped outward groove on the wall of the outlet end face of the inlet pipe;
step three, sequentially completing the welding of the inner welding seam of the first Y-shaped inward groove and the second Y-shaped inward groove, the welding of the outer welding seam of the first Y-shaped outward groove and the third Y-shaped outward groove, the welding of the outer welding seam of the second Y-shaped outward groove and the fourth Y-shaped outward groove, and the welding of the fillet of the baffle and the collector;
step four, processing a positioning groove on the cylindrical surface of the joint of the shell body and the flange;
and step five, welding the shell body and the flange into a whole through the electron beam.
Further, in the third step, argon arc welding is adopted to perform welding in sequence.
Compared with the prior art, the technical scheme of the invention has the advantages that:
1. the prepressing turbine inlet shell provided by the invention integrates the shell body, the inlet pipe, the collector, the baffle and the flange through a welding connection mode, the structure is compact, and the inlet pipe is provided with an inner and outer combined groove mode, so that high-quality welding with the collector is realized, and the problem that the tangential inlet pipe cannot realize high-reliability welding is solved.
2. The shell body and the flange are of a split structure, and the supersonic nozzle is machined in a split state, so that the high-precision machining requirement is met. Adopt the electron beam with casing body and flange welding as an organic whole, and electron beam welding seam top sets up the constant head tank, can guarantee electron beam accurate positioning when the welding. The adopted electron beam welding has high energy density, small molten metal range and small welding deformation, and can ensure that the position degree of the interfaces of the nozzle and the inlet pipe which are processed in advance is not influenced by the welding deformation basically.
Drawings
FIG. 1 is a schematic structural view of a precompressed turbine inlet housing of the present invention;
FIG. 2 is a cross-sectional view A-A of FIG. 1;
FIG. 3 is an enlarged partial schematic view of FIG. 2;
FIG. 4 is a partially enlarged view of the electron beam weld at I of FIG. 3;
FIG. 5 is a top view of FIG. 1;
FIG. 6 is an enlarged partial view of the composite weld at J of FIG. 5;
FIG. 7 is a cross-sectional view B-B of FIG. 5;
fig. 8 is a partially enlarged schematic view of the sectional positions of the housing body and the flange at K in fig. 7.
Reference numerals: 1-a shell body, 2-a collector, 3-a baffle, 4-a flange, 5-an inlet pipe, 6-a first Y-shaped inward bevel, 7-a supersonic nozzle, 8-a first Y-shaped outward bevel, 9-a second Y-shaped outward bevel, 11-a third Y-shaped outward bevel, 12-a second Y-shaped inward bevel, 13-a fourth Y-shaped outward bevel, 14-an electron beam weld, 15-a positioning groove, 21-a first connecting section, 22-a second connecting section.
Detailed Description
The invention is described in further detail below with reference to the figures and specific embodiments.
The invention provides a prepressing turbine inlet shell and a processing method thereof.A prepressing turbine inlet part is designed into a combined body structure that a shell body 1, an inlet pipe 5, a collector 2, a baffle 3 and a flange 4 are integrated, the inlet pipe 5 is provided with an inner and outer combined groove form, high-quality welding with the collector 2 is realized, and the problem that the tangential inlet pipe 5 cannot realize high-reliability welding is solved. The essence of the invention is that the prepressing turbine inlet shell with reliable performance and easier realization of the process is obtained by combining groove welding and electron beam welding. The inlet shell of the pre-pressing turbine is successfully subjected to verification tests on products, and can be widely applied to design of the pre-pressing turbine pump for the rocket engine and design of a combined body structure with similar characteristics.
As shown in fig. 1 to 8, the inlet housing of the pre-compressed turbine of the present invention includes a housing body 1, a flange 4, a collector 2, a baffle 3 and an inlet pipe 5, wherein the housing body 1 is a circular sleeve structure, and the flange 4 is disposed below the housing body 1 and is coaxial with the housing body 1; the collector 2 comprises a first connecting section 21 and a second connecting section 22, the cross sections of which are semi-annular, the first connecting section 21 is fixedly arranged on the outer wall of the shell body 1 and is buckled with the second connecting section 22 to form an arc-shaped circular tube; the inlet of the arc-shaped round pipe is arranged along the tangential direction of the shell body 1 and is communicated with the outlet of the inlet pipe 5, the outlet is sealed by the baffle 3, and the inlet of the inlet pipe 5 is a prepressing turbine driving medium inlet. The junction of the first connecting section 21 and the housing body 1 is provided with a plurality of supersonic nozzles 7, the supersonic nozzles 7 extend from the inner surface of the first connecting section 21 to the inner end surface of the housing body 1, and the center lines of the supersonic nozzles 7 and the end surface of the flange 4 are obliquely arranged, so that the inlets of the supersonic nozzles 7 are communicated with the inner cavity of the collector 2, and the outlets of the supersonic nozzles are communicated with the inner cavity of the housing body 1. A first Y-shaped outward groove 8 is formed in the side wall of the first connecting section 21, and a first Y-shaped inward groove 6 is formed in the end wall; a third Y-shaped outward groove 11 is formed in the side wall of the second connecting section 22, and a second Y-shaped outward groove 9 is formed in the end wall of the second connecting section; a second Y-shaped inward groove 12 matched with the first Y-shaped inward groove 6 and a fourth Y-shaped outward groove 13 matched with the second Y-shaped outward groove 9 are formed in the wall of the outlet end face of the inlet pipe 5; the first connecting section 21 and the second connecting section 22 are welded through a first Y-shaped outward groove 8 and a third Y-shaped outward groove 11; one end of the first connecting section 21 is welded with the inlet pipe 5 through a first Y-shaped inward groove 6 and a second Y-shaped inward groove 12, and the other end of the first connecting section is connected with the baffle 3 through a fillet weld; one end of the second connecting section 22 is welded with the inlet pipe 5 through a second Y-shaped outward groove 9 and a fourth Y-shaped outward groove 13, and the other end of the second connecting section is connected with the baffle 3 through a fillet weld; the shell body 1 and the flange 4 are connected into a whole through electron beam welding, and a positioning groove 15 is arranged on the cylindrical surface of an electron beam welding line 14 of the shell body 1 and the flange 4.
According to the invention, the boundary angle of the first Y-shaped outward groove 8 is 80-90 degrees, beta is 110-130 degrees, the wrap angle of the second Y-shaped inward groove 12 of the inlet pipe 5 is alpha + beta, the wrap angle of the fourth Y-shaped outward groove 13 is gamma is 360-alpha-beta, and the boundary angle alpha + beta is the wrap angle of the Y-shaped inward groove, so that when the first Y-shaped inward groove 6 and the second Y-shaped inward groove 12 are welded, the butt weld groove faces the outer side of the shell body 1, the problems that a welding gun is interfered with the shell body 1, the inclination angle of the welding gun is large and the like during welding are avoided, the problem that groove welding cannot be realized due to the space limitation problem is solved, the quality of the welding line is ensured, and the product reliability of the inlet shell body 1 is improved.
According to the invention, before the shell body 1 and the flange 4 are welded, the shell body 1, the inlet pipe 5, the collector 2 and the baffle 3 are welded, the shell body 1 and the flange 4 are connected by adopting an electron beam welding mode with high energy density and small welding deformation, and the positioning groove 15 is arranged at the top of the electron beam welding line 14, so that the electron beam can be accurately positioned during welding. Because the electron beam welding has high energy density, small molten metal range and small welding deformation, the interface positions of the supersonic nozzle 7 and the inlet pipe 5 which are processed in advance can be ensured not to be influenced by the welding deformation basically.
According to the invention, the minimum distance e at the intersection point of the nozzle outlet extension line and the shell body inner cavity surface is required to be ensured to be larger than 0.5mm by arranging the position of the electron beam welding seam 14 between the shell body 1 and the flange 4, so that the arrangement can ensure the operation space of the outlet section of the electric spark machining supersonic nozzle 7 and can avoid the electric corrosion to the shell body 1.
According to the invention, the positioning groove 15 is arranged on the cylindrical surface at the outer diameter of the electron beam welding seam 14, the positioning groove 15 is composed of a shell body half groove and a flange half groove structure, and when the depth h and the width l of the half groove are within the range of 0.5-0.7 mm, the electron beam can be ensured to be accurately positioned during welding without influencing the welding seam structure and quality.
Meanwhile, the invention also provides a processing method of the pre-pressed turbine inlet shell, which comprises the following steps:
firstly, processing a first connecting section 21 on the outer cylindrical surface of a shell body 1, and processing a supersonic nozzle 7 at the joint of the first connecting section 21 and the shell body 1;
step two, processing a first Y-shaped outward groove 8 on the side wall of the first connecting section 21, and processing a first Y-shaped inward groove 6 on the end wall; a third Y-shaped outward groove 11 is machined on the side wall of the second connecting section 22, and a second Y-shaped outward groove 9 is machined on the end wall; a second Y-shaped inward groove 12 and a fourth Y-shaped outward groove 13 are machined on the wall of the outlet end face of the inlet pipe 5;
thirdly, performing inner seam welding of a first Y-shaped inward groove 6 and a second Y-shaped inward groove 12, outer seam welding of a first Y-shaped outward groove 8 and a third Y-shaped outward groove 11, outer seam welding of a second Y-shaped outward groove 9 and a fourth Y-shaped outward groove 13, and fillet welding of a baffle 3 and a collector 2 in sequence by adopting argon arc welding;
step four, processing a positioning groove 15 on the cylindrical surface of the joint of the shell body 1 and the flange 4;
and step five, welding the shell body 1 and the flange 4 into a whole through electron beams.
Claims (6)
1. A pre-pressing turbine inlet shell comprises a shell body (1), a flange (4), a collector (2), a baffle (3) and an inlet pipe (5),
the shell body (1) is of a circular sleeve structure, and the flange (4) is arranged below the shell body (1) and is coaxial with the shell body (1);
the collector (2) comprises a first connecting section (21) and a second connecting section (22) of which the cross sections are semi-annular, wherein the first connecting section (21) is fixedly arranged on the outer wall of the shell body (1) and is buckled with the second connecting section (22) to form an arc-shaped circular tube;
the inlet of the arc-shaped circular tube is tangentially arranged along the shell body (1) and is communicated with the outlet of the inlet pipe (5), and the outlet is sealed by the baffle (3);
a plurality of supersonic nozzles (7) are arranged at the joint of the first connecting section (21) and the shell body (1), the inlets of the supersonic nozzles (7) are communicated with the inner cavity of the collector (2), the outlets of the supersonic nozzles are communicated with the inner cavity of the shell body (1), and the center lines of the supersonic nozzles (7) and the end face of the flange (4) are obliquely arranged;
a first Y-shaped outward groove (8) is formed in the side wall of the first connecting section (21), and a first Y-shaped inward groove (6) is formed in the end wall of the first connecting section;
a third Y-shaped outward groove (11) is formed in the side wall of the second connecting section (22), and a second Y-shaped outward groove (9) is formed in the end wall of the second connecting section;
a second Y-shaped inward groove (12) matched with the first Y-shaped inward groove (6) and a fourth Y-shaped outward groove (13) matched with the second Y-shaped outward groove (9) are formed in the wall of the outlet end face of the inlet pipe (5);
the first connecting section (21) and the second connecting section (22) are welded through a first Y-shaped outward groove (8) and a third Y-shaped outward groove (11);
one end of the first connecting section (21) is welded with the inlet pipe (5) through a first Y-shaped inward groove (6) and a second Y-shaped inward groove (12), and the other end of the first connecting section is connected with the baffle (3) through a fillet weld;
one end of the second connecting section (22) is welded with the inlet pipe (5) through a second Y-shaped outward groove (9) and a fourth Y-shaped outward groove (13), and the other end of the second connecting section is connected with the baffle (3) through a fillet weld;
the shell body (1) and the flange (4) are connected into a whole through electron beam welding, and a positioning groove (15) is formed in the cylindrical surface of an electron beam welding line (14) of the shell body (1) and the flange (4).
2. The precompression turbine inlet casing as claimed in claim 1, wherein: and the minimum distance e between the position of the electron beam welding seam between the shell body (1) and the flange (4) and the intersection point of the extension line of the outlet of the supersonic nozzle (7) and the inner cavity surface of the shell body is greater than 0.5 mm.
3. The pre-compressed turbine inlet casing according to claim 1 or 2, wherein: the boundary angle of the first Y-shaped outward groove (8) is 80-90 degrees, beta is 110-130 degrees, the wrap angle of the second Y-shaped inward groove (12) is alpha + beta, and the wrap angle of the fourth Y-shaped outward groove (13) is gamma 360-alpha-beta.
4. The precompression turbine inlet casing as claimed in claim 3, wherein: the positioning groove (15) comprises a shell body half groove and a flange half groove which are matched, and the depth and the width of the shell body half groove and the flange half groove are both 0.5 mm-0.7 mm.
5. A processing method of a pre-pressing turbine inlet shell is characterized by comprising the following steps:
step one, processing a first connecting section on the outer cylindrical surface of a shell body, and processing a supersonic nozzle at the joint of the first connecting section and the shell body;
step two, processing a first Y-shaped outward groove on the side pipe wall of the first connecting section, and processing a first Y-shaped inward groove on the end pipe wall; processing a third Y-shaped outward groove on the side pipe wall of the second connecting section, and processing a second Y-shaped outward groove on the end pipe wall; processing a second Y-shaped inward groove and a fourth Y-shaped outward groove on the wall of the outlet end face of the inlet pipe;
step three, sequentially completing the welding of the inner welding seam of the first Y-shaped inward groove and the second Y-shaped inward groove, the welding of the outer welding seam of the first Y-shaped outward groove and the third Y-shaped outward groove, the welding of the outer welding seam of the second Y-shaped outward groove and the fourth Y-shaped outward groove, and the welding of the fillet of the baffle and the collector;
step four, processing a positioning groove on the cylindrical surface of the joint of the shell body and the flange;
and step five, welding the shell body and the flange into a whole through the electron beam.
6. The method for machining a pre-compressed turbine inlet casing according to claim 5, wherein: and in the third step, argon arc welding is adopted for welding in sequence.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011011616.0A CN112196632B (en) | 2020-09-23 | 2020-09-23 | Prepressing turbine inlet shell and machining method thereof |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011011616.0A CN112196632B (en) | 2020-09-23 | 2020-09-23 | Prepressing turbine inlet shell and machining method thereof |
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| CN112196632A true CN112196632A (en) | 2021-01-08 |
| CN112196632B CN112196632B (en) | 2023-01-20 |
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| CN113431708A (en) * | 2021-05-31 | 2021-09-24 | 西安航天动力研究所 | Turbine shell with cooling structure and machining method |
| CN116291960A (en) * | 2023-04-23 | 2023-06-23 | 北京星河动力装备科技有限公司 | Gas collecting structure, turbo pump and rocket engine |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| Publication number | Publication date |
|---|---|
| CN112196632B (en) | 2023-01-20 |
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