CN113775533B - A turbopump device for rocket engines - Google Patents

Abstract

The invention discloses a turbine pump device for a rocket engine, which comprises a shell (1), a centrifugal impeller (2) and a connecting shaft assembly (3), wherein main blades and spiral induction blades are arranged on the periphery of a hub, and the turbine pump device is characterized in that: the connecting shaft assembly comprises a first shaft (31) and a second shaft (32), wherein the left end of the first shaft is provided with a step part (37), the step part is inserted into a corresponding step hole of the hub, the left end of the first shaft is provided with a first threaded hole, a first screw rod (33) is connected in the first threaded hole, the left end of the first screw rod is provided with a shoulder head part (36), the shoulder head part is provided with an extrusion conical surface (38), the second threaded hole is connected with a second screw rod (34), and the left end of the second screw rod is connected with a diversion cap (35). The invention has the advantages of high connection strength and convenient installation/disassembly; by means of the design of the grooves and/or the auxiliary guide vanes, the pressure loss of the diffuser can be reduced, and therefore the outlet pressure of the turbine pump is improved.

Description

A turbopump device for rocket engines

Technical field

The present invention relates to the technical field of rocket engines, and in particular to a turbopump device for rocket engines.

Background technique

The turbopump of a rocket engine is mainly composed of an inducer, a centrifugal impeller, a mechanical seal, a bearing, a shafting support system and a casing. However, existing turbine pump devices have problems such as insufficient installation strength of the impeller, inconvenient installation/disassembly, and large pump outlet pressure loss.

Contents of the invention

The purpose of the present invention is to overcome the deficiencies in the prior art and provide a turbopump device for a rocket engine. Through the design of the connecting shaft assembly, compared with the existing impeller mounting structure, it has the advantages of high connection strength and easy installation. /The advantage of easy disassembly. Through the design of grooves and/or auxiliary guide vanes, it can reduce the pressure loss of the diffuser and allow the liquid flow to flow to the volute outlet pipe in an orderly manner, thereby increasing the outlet pressure of the turbine pump and reducing the power loss of the turbine pump.

In order to achieve the above objects, the technical solutions adopted by the present invention are:

A turbopump device for a rocket engine, which includes a casing (1), a centrifugal impeller (2), and a connecting shaft assembly (3). The centrifugal impeller is installed in the pump cavity of the casing, and the centrifugal impeller is installed through the connecting shaft assembly. On the casing, the centrifugal impeller includes a hub (21). The outer periphery of the hub is provided with a main blade (22) and a spiral induction blade (23). The spiral induction blade is located upstream of the main blade. It is characterized by: a connecting shaft assembly (3) It includes a first shaft (31) and a second shaft (32). The left end of the second shaft is inserted into the stepped concave hole on the right end of the first shaft. The right end of the second shaft is connected to the combustion part or injection part of the engine. The first shaft The left end has a step portion (37), which is inserted into the corresponding step hole of the hub. The left end of the first shaft has a first threaded hole. A first screw (33) is connected to the first threaded hole. The left end of the first screw has a shoulder. part (36), the shoulder part has an extrusion tapered surface (38), the extrusion tapered surface matches the corresponding tapered surface of the hub, the right end of the first screw has a second threaded hole, and the second threaded hole is connected with a third Two screws (34), the left end of the second screw is connected with a diversion cap (35).

Further, the left end of the hub (21) is provided with a connecting cavity (24), the shoulder portion (36) and the second screw (34) are located in the connecting cavity, and the outer periphery of the first shaft (31) is provided with a keyway and a connecting key. (25), the first shaft is connected to the hub through a connecting key, and the tapered surface of the hub that matches the extruded tapered surface (38) is arranged adjacent to the stepped concave hole.

Further, the pump chamber of the housing (1) has a front side wall (11) and a rear side wall (12) arranged oppositely, and a diffuser guide vane (13) is provided between the front side wall and the rear side wall. , multiple diffuser guide vanes are evenly distributed along the circumferential direction. The diffuser guide vanes are located radially outside the centrifugal impeller (2). The front side wall and the rear side wall include a first inclined portion (14) and a convex portion connected in sequence. The raised portion (16) and the second inclined portion (15), the first inclined portion, the convex portion and the second inclined portion are connected in sequence along the radial direction, on the rear side wall (12) between adjacent diffuser guide vanes. A groove (17) is provided, which is formed in a concave manner to remove material.

Further, one or more auxiliary guide vanes (18) are provided in the groove (17).

Further, both the radially inner end and the radially outer end of the groove (17) are arc-shaped parts.

Further, the axial depth of the groove (17) gradually increases from the radially inner end to the radially outer end.

Further, two auxiliary guide vanes (18) are provided between adjacent diffuser guide vanes (13). The inner radius of the auxiliary guide vanes is equal to the inner radius of the diffuser guide vanes, and the outer radius of the auxiliary guide vanes is equal to the inner radius of the diffuser guide vanes. It is not equal to the outer radius of the diffuser guide vane; and the diffuser guide vane has an outer radius R, the auxiliary guide vane has an outer radius R1, R1<R, and R1=(0.70-0.97)R.

Furthermore, the blade shape of the diffuser guide vanes (13) is different from the blade shape of the auxiliary guide vanes (18), and the blade thickness of the diffuser guide vanes gradually increases along the direction of the liquid flow, and the blades of the auxiliary guide vanes are Leaves are of equal thickness.

Further, the inducer includes a spiral induction blade (23). The spiral induction blade includes a plurality of first spiral blades (231) and a plurality of splitting spiral blades (232). The splitting spiral blades are arranged between the first spiral blades, and the splitting spiral blades are arranged between the first spiral blades. The blade inlet angle of the blade is greater than the blade inlet angle of the first spiral blade, and the blade outlet angle of the splitting spiral blade is greater than the blade exit angle of the first spiral blade, and the magnitude relationship is 1.05-1.3 times.

The turbopump device for a rocket engine of the present invention has the advantages of high connection strength and convenient installation/disassembly compared with the existing impeller installation structure through the design of the connecting shaft assembly. Through the design of grooves and/or auxiliary guide vanes, it can reduce the pressure loss of the diffuser and allow the liquid flow to flow to the volute outlet pipe in an orderly manner, thereby increasing the outlet pressure of the turbine pump and reducing the power loss of the turbine pump. In the inducer of the present invention, the splitter spiral blades are offset and independently designed. The inlet and outlet angles of the splitter blades are slightly larger than the inlet and outlet angles of the first spiral blades, which can prevent the inlet blades of the inducer from being clogged and at the same time improve the total lift of the inducer. .

Description of the drawings

Figure 1 is a schematic structural diagram of a turbopump device for a rocket engine according to the present invention (a partial structural diagram of the turbopump);

Figure 2 is a partially enlarged structural schematic diagram of a turbopump device for a rocket engine according to the present invention;

Figure 3 is a schematic side structural view of a turbopump device for a rocket engine according to the present invention;

Figure 4 is a schematic structural diagram of an inducer of a turbopump device for a rocket engine according to the present invention.

In the figure: casing 1, centrifugal impeller 2, connecting shaft assembly 3, front side wall 11, rear side wall 12, diffuser guide vane 13, first inclined part 14, second inclined part 15, raised part 16, Groove 17, auxiliary guide vane 18, hub 21, main blade 22, spiral induction blade 23, connecting cavity 24, connecting key 25, first shaft 31, second shaft 32, first screw 33, second screw 34, guide The flow cap 35 , the shoulder part 36 , the step part 37 , the extrusion tapered surface 38 , the first spiral blade 231 , and the splitting spiral blade 232 .

Detailed ways

In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments These are some embodiments of the present invention, rather than all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without making creative efforts fall within the scope of protection of the present invention.

The present invention will be further described in detail below in conjunction with the accompanying drawings.

As shown in Figure 1-4, a turbopump device for a rocket engine includes a casing 1, a centrifugal impeller 2, and a connecting shaft assembly 3. The centrifugal impeller 2 is installed in the pump chamber of the casing 1. The centrifugal impeller 2 Installed on the casing 1 through the connecting shaft assembly 3, the centrifugal impeller 2 includes a hub 21. The outer periphery of the hub 21 is provided with a main blade 22 and a spiral induction blade 23. The spiral induction blade 23 is located upstream of the main blade 22. It is characterized by: connection The shaft assembly 3 includes a first shaft 31 and a second shaft 32. The left end of the second shaft 32 is inserted into the stepped concave hole on the right end of the first shaft 31. The right end of the second shaft 32 is connected to the combustion part or injection part of the engine. The first The left end of the shaft 31 has a step portion 37, which is inserted into the corresponding step hole of the hub 21. The left end of the first shaft 31 has a first threaded hole, and a first screw rod 33 is connected in the first threaded hole. The left end has a shoulder portion 36. The shoulder portion 36 has an extrusion tapered surface 38. The extrusion tapered surface 38 matches the corresponding tapered surface of the hub 21. The right end of the first screw rod 33 has a second threaded hole. A second screw 34 is connected, and the left end of the second screw 34 is connected to a guide cap 35. The left end of the hub 21 is provided with a connection cavity 24. The shoulder portion 36 and the second screw 34 are located in the connection cavity 24. The outer circumference of the first shaft 31 A keyway and a connecting key 25 are provided. The first shaft 31 is connected to the hub 21 through the connecting key 25. The tapered surface of the hub 21 that matches the extruded tapered surface 38 is arranged adjacent to the stepped concave hole.

The centrifugal impeller 2 is a semi-open impeller, and the turbine pump is used to pump liquid fuels such as low-temperature methane or low-temperature liquid oxygen.

A turbopump device for a rocket engine of the present invention, through the design of the connecting shaft assembly 3, has the advantages of high connection strength and convenient installation/disassembly compared with the existing impeller installation structure.

The first screw 33 and the guide cap 35 are provided with wrench grooves for operating wrench tools.

Further, as shown in Figures 2-3, the pump chamber of the housing 1 has a front side wall 11 and a rear side wall 12 arranged oppositely, and a diffuser guide vane 13 is provided between the front side wall 11 and the rear side wall 12. , a plurality of diffuser guide vanes 13 are evenly distributed along the circumferential direction. The diffuser guide vanes 13 are located radially outside the centrifugal impeller 2. The front side wall 11 and the rear side wall 12 include a first inclined portion 14 and a convex portion connected in sequence. The raised portion 16, the second inclined portion 15, the first inclined portion 14, the protruding portion 16, and the second inclined portion 15 are connected in sequence along the radial direction. The rear side wall 12 between adjacent diffuser guide vanes 13 is provided with The groove 17 is formed by removing material in a concave manner, and one or more auxiliary guide vanes 18 are disposed in the groove 17 .

A turbopump device for a rocket engine of the present invention can reduce the pressure loss of the diffuser through the design of the groove 17 and/or the auxiliary guide vane 18, so that the liquid flow can flow to the volute outlet pipe in an orderly manner. Thereby increasing the outlet pressure of the turbine pump and reducing the power loss of the turbine pump.

Furthermore, both the radially inner end and the radially outer end of the groove 17 are arc-shaped parts, which has a better flow guiding effect.

Furthermore, the axial depth of the groove 17 gradually increases from the radially inner end to the radially outer end, which can further reduce the pressure loss of the diffuser.

Further, two auxiliary guide vanes 18 are provided between adjacent diffuser guide vanes 13. The inner radius of the auxiliary guide vanes 18 is equal to the inner radius of the diffuser guide vanes 13, and the outer radius of the auxiliary guide vanes 18 is equal to that of the diffuser guide vanes 13. The outer radii of the diffuser guide vanes 13 are unequal; the diffuser guide vanes 13 have an outer radius R, and the auxiliary guide vanes 18 have an outer radius R1, R1<R, R1=(0.80-0.95)R, preferably R1=0.85 -0.90R.

The blade shape of the diffuser guide vane 13 is different from the blade shape of the auxiliary guide vane 18. The blade thickness of the diffuser guide vane 13 gradually increases along the liquid flow, while the blades of the auxiliary guide vane 18 are uniformly thick blades.

As shown in Figure 4, the inducer includes a spiral induction blade 23. The spiral induction blade 23 includes a plurality of first spiral blades 231 and a plurality of splitting spiral blades 232. The splitting spiral blades 232 are arranged between the first spiral blades 231; the splitting spiral The blade entrance angle of the blade 232 is slightly larger than the blade entrance angle of the first spiral blade 231, and the blade exit angle of the splitting spiral blade 232 is slightly larger than the blade exit angle of the first spiral blade 231, such as 1.05-1.3 times. In the inducer of the present invention, the splitter spiral blade 232 is designed to be offset and independently designed. The inlet and outlet angle of the splitter blade 232 is slightly larger than the inlet and outlet angle of the first spiral blade 231, which can prevent the inlet blade of the inducer from being clogged and at the same time improve the total length of the inducer. Lift effect.

A turbopump device for a rocket engine of the present invention, through the design of the connecting shaft assembly 3, has the advantages of high connection strength and convenient installation/disassembly compared with the existing impeller installation structure. Through the design of the groove 17 and/or the auxiliary guide vane 18, the pressure loss of the diffuser can be reduced, allowing the liquid flow to flow to the volute outlet pipe in an orderly manner, thereby increasing the outlet pressure of the turbine pump and reducing the power loss of the turbine pump. .

The above-mentioned embodiments are illustrative of the present invention, not limitations of the present invention. It can be understood that various changes, modifications, substitutions and modifications can be made to these embodiments without departing from the principles and spirit of the present invention. The protection scope of the present invention as defined by the appended claims and their equivalents.

Claims (4)

1. The utility model provides a turbopump device for rocket engine, it includes casing (1), centrifugal impeller (2), connecting axle subassembly (3), and centrifugal impeller is installed to the pump intracavity of casing, and centrifugal impeller passes through connecting axle subassembly to be installed on the casing, and centrifugal impeller includes wheel hub (21), and wheel hub's periphery is equipped with main blade (22), spiral induction blade (23), and spiral induction blade is located the upper reaches of main blade, its characterized in that: the connecting shaft assembly (3) comprises a first shaft (31) and a second shaft (32), wherein the left end of the second shaft is inserted into a stepped concave hole at the right end of the first shaft, the right end of the second shaft is connected with a combustion part or a spraying part of an engine, the left end of the first shaft is provided with a stepped part (37), the stepped part is inserted into a corresponding stepped hole of a hub, the left end of the first shaft is provided with a first threaded hole, the first threaded hole is connected with a first screw rod (33), the left end of the first screw rod is provided with a shoulder part (36), the shoulder part is provided with an extrusion conical surface (38), the extrusion conical surface is matched with a corresponding conical surface of the hub, the left end of the first screw rod is provided with a second threaded hole, the second threaded hole is connected with a second screw rod (34), and the left end of the second screw rod is connected with a flow guide cap (35);

the pump cavity of the shell (1) is provided with a front side wall (11) and a rear side wall (12) which are oppositely arranged, diffuser guide vanes (13) are arranged between the front side wall and the rear side wall, the diffuser guide vanes are uniformly distributed along the circumferential direction, the diffuser guide vanes are positioned on the radial outer side of the centrifugal impeller (2), the front side wall and the rear side wall comprise a first inclined part (14), a protruding part (16) and a second inclined part (15) which are sequentially connected, the first inclined part, the protruding part and the second inclined part are sequentially connected along the radial direction, a groove (17) is formed in the rear side wall (12) between the adjacent diffuser guide vanes, and the groove is formed in a material removing way in a concave manner; one or more auxiliary guide vanes (18) are arranged in the groove (17); the radial inner end and the radial outer end of the groove (17) are arc-shaped parts; the axial depth of the groove (17) gradually increases from the radial inner end to the radial outer end; the blade profile of the diffuser guide vane (13) is different from that of the auxiliary guide vane (18), the thickness of the blade of the diffuser guide vane is gradually increased along the direction of liquid flow, and the blade of the auxiliary guide vane is an equal-thickness blade.

2. A turbopump device for rocket engines according to claim 1, characterized in that the left end of the hub (21) is provided with a connecting cavity (24), the shoulder head (36) and the second screw (34) are located in the connecting cavity, the periphery of the first shaft (31) is provided with a key slot and a connecting key (25), the first shaft is connected with the hub through the connecting key, and the conical surface of the hub matched with the extrusion conical surface (38) is arranged adjacent to the stepped concave hole.

3. A turbopump device for rocket engines according to claim 2, characterized in that two auxiliary vanes (18) are arranged between adjacent diffuser vanes (13), the inner radius of which is equal to the inner radius of the diffuser vanes, and the outer radius of which is unequal to the outer radius of the diffuser vanes; and the diffuser vane has an outer radius R, the auxiliary vane has an outer radius R1, R1 < R, and r1= (0.70-0.97) R.

4. A turbopump device for rocket engines according to claim 2 or 3, characterized in that the inducer comprises a spiral inducer blade (23) comprising a plurality of first spiral blades (231), a plurality of splitter spiral blades (232) arranged between the first spiral blades, the splitter spiral blades having a blade inlet angle greater than the blade inlet angle of the first spiral blades, the splitter spiral blades having a blade outlet angle greater than the blade outlet angle of the first spiral blades, and the size relationship being 1.05-1.3 times.