Turbine and applied liquid rocket engine turbine pump

Abstract

The invention discloses a turbine, and relates to the technical field of turbine pumps of liquid rocket engines. The turbine comprises a turbine shell, a turbine disc, a guide ring and a turbine outlet pipe; the turbine outlet pipe is fixed to the turbine shell, and the turbine shell and the turbine outlet pipe are provided with mortise structures used for radial positioning. The guide ring is located in the turbine outlet pipe and fixed to the turbine shell. An outer spigot used for radial positioning is arranged between the guide ring and the turbine shell. The turbine disc is located in the guide ring, and a labyrinth sealing groove corresponding to the turbine disc is formed in the inner side of the guide ring. According to the turbine, the guide ring and the turbine shell are positioned through the outer spigot, the turbine shell and the turbine outlet are positioned through the mortise structure, mounting and dismounting are convenient, the labyrinth seal groove structure is arranged on the guide ring, the high-temperature gas leakage rate can be reduced, and the turbine efficiency is improved.

Description

Technical Field

[0001] The invention relates to the technical field of liquid rocket engine turbo pumps, and in particular to a turbine and an applied liquid rocket engine turbo pump. Background Art

[0002] The turbine of a turbopump is a structural component that provides rotational power to the turbopump. At present, most turbopump turbines are connected to the turbine shaft using spline connections or pin connections, the guide ring is positioned by an internal stop, the guide ring is not provided with a sealing structure, and the turbine outlet pipe is welded to the turbine housing. The above structures have the disadvantages of low reliability, complex assembly process, large turbine gas leakage, and difficulty in maintenance. Summary of the invention

[0003] In view of the above problems, the present invention has developed a turbine for a liquid rocket engine turbopump, which can avoid the above disadvantages while achieving the same function.

[0004] The technical solution of the present invention is as follows:

[0005] A turbine comprises a turbine housing, a turbine disk, a guide ring and a turbine outlet pipe;

[0006] The turbine outlet pipe is fixed to the turbine housing, and the turbine housing and the turbine outlet pipe are provided with a tongue-and-groove structure for radial positioning;

[0007] The guide ring is located in the turbine outlet pipe and fixed on the turbine housing; an outer stop for radial positioning is provided between the guide ring and the turbine housing;

[0008] The turbine disc is located in the guide ring, and the inner side of the guide ring is provided with a labyrinth sealing groove corresponding to the turbine disc.

[0009] Preferably, the outer edge of the turbine disc is provided with primary blades and secondary blades in the radial direction; the inner side of the guide ring is provided with primary blade labyrinth sealing grooves and secondary blade labyrinth sealing grooves corresponding to the primary blades and secondary blades respectively.

[0010] Preferably, a sealing gasket is provided in the tongue-and-groove structure of the turbine housing and the turbine outlet pipe. More preferably, the depth of the tongue-and-groove structure exceeds 7 mm.

[0011] In some other embodiments, the turbine outlet pipe and guide ring are both installed and fixed on the turbine casing through detachable parts.

[0012] Furthermore, an air collecting ring and a nozzle ring are arranged on the turbine housing, and the nozzle ring is circumferentially arranged around the air collecting ring.

[0013] In some other embodiments, the guide ring is composed of three parts spliced ​​together.

[0014] The present invention also provides a liquid rocket engine turbo pump, comprising a pump shaft, a fuel pump housing and the above-mentioned turbine;

[0015] The turbine housing is fixedly connected to the fuel pump housing; the pump shaft is fixedly connected to the turbine disk, and the turbine disk can drive the pump shaft to rotate.

[0016] Preferably, the pump shaft is connected to the turbine disc via a detachable part, and an inner hole is provided at the end of the pump shaft, a boss corresponding to the inner hole is provided on the turbine disc, and the inner hole and the boss are connected by interference fit.

[0017] Furthermore, the turbine housing and the fuel pump housing are fixedly connected via a detachable part, and the turbine housing and the fuel pump housing are provided with a tongue-and-groove structure for radial positioning. Preferably, a sealing gasket is provided in the tongue-and-groove structure of the turbine housing and the fuel pump housing.

[0018] The turbine of the present invention has a turbine housing and a turbine outlet pipe provided with a tongue and groove structure for radial positioning, an outer stop for radial positioning is provided between the guide ring and the turbine housing, a labyrinth sealing groove corresponding to the turbine disk is provided on the inner side of the guide ring, the guide ring and the turbine housing are positioned with the outer stop, and the turbine housing and the turbine outlet are positioned with the tongue and groove structure, which is convenient for installation and disassembly, and the labyrinth sealing groove structure provided on the guide ring can reduce the leakage of high-temperature combustion gas and improve the efficiency of the turbine. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other accompanying drawings can be obtained based on these accompanying drawings without paying any creative work.

[0020] Figure 1 It is a cross-sectional view of a liquid rocket engine turbopump according to an embodiment of the present invention.

[0021] Figure 2 1 is a structural diagram of a turbine casing according to an embodiment of the present invention.

[0022] Figure 3 1 is a structural diagram of a turbine disk according to an embodiment of the present invention.

[0023] Figure 4 This is a structural diagram of a guide ring according to an embodiment of the present invention.

[0024] Explanation of the markings in the figure: 1- pump shaft; 2- fuel pump housing; 3- first bolt; 4- first gasket; 5- turbine housing; 6- second gasket; 7- second bolt, 8- third bolt; 9- guide ring; 10- turbine disk; 11- fourth bolt; 12- nut; 13- turbine outlet pipe; 51- gas collecting ring; 52- nozzle ring; 53- weld; 54- mortise and tenon; 55- external stop; 511- turbine gas inlet; 101- first-stage blade; 102- second-stage blade; 103- boss; 91- first-stage blade labyrinth sealing groove; 92- second-stage blade labyrinth sealing groove; 93- first component; 94- second component; 95- third component; 96- cutting seam. DETAILED DESCRIPTION

[0025] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0026] It should be understood that when used in this specification and the appended claims, the terms "include" and "comprises" indicate the presence of described features, integers, steps, operations, elements and / or components, but do not exclude the presence or addition of one or more other features, integers, steps, operations, elements, components and / or combinations thereof.

[0027] It should also be understood that the terms used in this specification of the present invention are only for the purpose of describing specific embodiments and are not intended to limit the present invention. As used in the specification of the present invention and the appended claims, unless the context clearly indicates otherwise, the singular forms "a", "an" and "the" are intended to include plural forms.

[0028] It should be further understood that the term "and / or" used in the present description and the appended claims refers to and includes any and all possible combinations of one or more of the associated listed items.

[0029] See also Figure 1-4 The liquid rocket engine turbopump shown includes a pump shaft 1, a fuel pump housing 2 and a turbine.

[0030] The turbine comprises a turbine housing 5 , a turbine disk 10 , a guide ring 9 and a turbine outlet pipe 13 .

[0031] The turbine outlet pipe 13 is fixed on the turbine housing 5, and the turbine housing 5 and the turbine outlet pipe 13 are provided with a tongue-and-groove structure for radial positioning. Specifically, the turbine outlet pipe 13 is fixed to the turbine housing 5 by a detachable part. In this embodiment, the detachable part is a plurality of second bolts 7, and the second bolts 7 are preferably hexagonal bolts, that is, the turbine outlet pipe 13 is fixed to the turbine housing 5 by a plurality of hexagonal bolts. In this embodiment, the tongue-and-groove structure provided in the turbine housing 5 and the turbine outlet pipe 13 includes a tongue-and-groove 54 provided on the turbine housing 5 and a tenon provided on the turbine outlet pipe 13 corresponding to the tongue-and-groove 54. The matching of the tongue-and-groove 54 and the tenon can realize the rapid positioning and installation of the turbine housing 5 and the turbine outlet pipe 13; a second sealing gasket 6 is also provided in the tongue-and-groove 54, and the second sealing gasket 6 is preferably a graphite sealing gasket, which is used for the compression and sealing of the tongue-and-groove structure; in practical applications, the depth of the tongue-and-groove 54 is preferably more than 7 mm. It can be understood that in some other embodiments, the tongue-and-groove can be provided on the turbine outlet pipe 13, and the tenon corresponding to the tongue-and-groove can be provided on the turbine housing 5.

[0032] The guide ring 9 is located in the turbine outlet pipe 13 and fixed on the turbine housing 5; an outer stop 55 for radial positioning is provided between the guide ring 9 and the turbine housing. Specifically, the guide ring 9 is fixed to the turbine housing 5 by a detachable part. In this embodiment, the detachable part is a plurality of third bolts 8, and the third bolts 8 are preferably hexagon socket head screws, that is, the guide ring 9 is fixed to the turbine housing 5 by a plurality of hexagon socket head screws. In this embodiment, the outer stop 55 is provided on the turbine housing 5, and an abutment portion matching the outer stop 55 is provided on the guide ring 9. The matching of the outer stop 55 and the abutment portion can realize the rapid positioning and installation of the turbine housing 5 and the guide ring 9. It can be understood that in some other embodiments, the outer stop 55 can be provided on the guide ring 9, and the abutment portion matching the outer stop 55 can be provided on the turbine housing 5.

[0033] In this embodiment, the guide ring 9 is composed of multiple parts. Specifically, the guide ring 9 is processed as a whole and then divided into three parts by wire cutting, such as Figure 4 As shown, the guide ring 9 is composed of a first component 93, a second component 94, and a third component 95. The central angle of each component is 120°, and there is a cutting seam 96 between adjacent components. The positioning of the outer stop 55 and the three-component structure are conducive to the installation and disassembly of the guide ring 9, and the guide ring 9 can be installed after the turbine rotor is installed in place.

[0034] The turbine disk 10 is located in the guide ring 9, and the inner side of the guide ring 9 is provided with a labyrinth seal groove corresponding to the turbine disk 10. Figure 3The turbine disk 10 shown is a single-disk two-stage turbine disk, and the outer edge is provided with a primary blade 101 and a secondary blade 102 in the radial direction. The two-stage blades help improve the turbine efficiency. The inner side of the guide ring 9 is provided with a primary blade labyrinth seal groove 91 and a secondary blade labyrinth seal groove 92 corresponding to the primary blade 101 and the secondary blade 102 respectively. The labyrinth seal groove structure can reduce the leakage of high-temperature fuel gas and improve the turbine efficiency.

[0035] The end of the pump shaft 1 extends to the inside of the turbine and is fixedly connected to the turbine disk 10, and the turbine disk 10 can drive the pump shaft 1 to rotate. Specifically, the pump shaft 1 and the turbine disk 10 are connected through a detachable part. In this embodiment, the detachable part is a plurality of fourth bolts 11 and nuts 12. The fourth bolts 11 are preferably reamed hole bolts, and the nuts 12 are preferably hexagonal nuts. That is, the pump shaft 1 and the turbine disk 10 are connected and fixed by a plurality of reamed hole bolts and hexagonal nuts. The reamed hole bolts play both the role of connection and fixing and the role of positioning pins for torque transmission. The structure is simple and reliable. In some other embodiments, the hexagonal nuts and the heads of the reamed hole bolts can be spot welded and locked to prevent loosening.

[0036] In addition, an inner hole is provided at the end of the pump shaft 1 , and a boss 103 corresponding to the inner hole is provided on the turbine disk, and the inner hole and the boss 103 are connected by interference fit.

[0037] Further, such as Figure 2 As shown, a gas collecting ring 51 and a nozzle ring 52 are provided on the turbine housing 5, and the nozzle ring 52 is circumferentially arranged around the gas collecting ring. A turbine gas inlet 511 is provided on the gas collecting ring 51. Preferably, the gas collecting ring 51 and the nozzle ring 52 are welded by argon arc welding and then machined to form a weld 53 on the turbine housing, and the turbine housing 5 is obtained after machining.

[0038] The turbine housing 5 is fixedly connected to the fuel pump housing 2. Specifically, the turbine housing 5 is fixedly connected to the fuel pump housing 2 through a detachable part. In this embodiment, the detachable part is a plurality of first bolts 3, and the first bolts 3 are preferably hexagonal bolts, that is, the turbine housing 5 is installed and fixed on the fuel pump housing 2 through a plurality of hexagonal bolts. In addition, the turbine housing 5 and the fuel pump housing 2 are provided with a mortise and tenon structure for radial positioning, and the mortise and tenon structure includes a mortise and tenon provided on the fuel pump housing 2 and a tenon corresponding to the mortise and tenon provided on the turbine housing 5. The matching of the mortise and tenon can realize the rapid positioning and installation of the turbine housing 5 and the fuel pump housing 2; a first sealing gasket 4 is also provided in the mortise and tenon, and the first sealing gasket 4 is preferably a graphite sealing gasket, which is used for compression sealing of the mortise and tenon structure.

[0039] The turbine of the liquid rocket engine turbopump of the present invention is provided with a tongue-and-groove structure for radial positioning on the turbine housing and the turbine outlet pipe, an outer stop for radial positioning is provided between the guide ring and the turbine housing, a labyrinth sealing groove corresponding to the turbine disk is provided on the inner side of the guide ring, the guide ring and the turbine housing are positioned by the outer stop, and the turbine housing and the turbine outlet are positioned by the tongue-and-groove structure, which is convenient for installation and disassembly, and the labyrinth sealing groove structure provided on the guide ring can reduce the leakage of high-temperature fuel gas and improve the efficiency of the turbine. In addition, the guide ring is divided into three petals by wire cutting after integral processing, and the outer stop is positioned, so that the guide ring is easy to install and disassemble; the turbine outlet pipe is fixed to the turbine housing by hexagonal bolts, a tongue-and-groove structure is provided on the turbine housing and the turbine outlet pipe, and a graphite sealing gasket is installed for compression sealing, and this structure has the advantages of convenient installation, reliable sealing, and reusable parts.

[0040] In the liquid rocket engine turbopump using this turbine, the pump shaft and the turbine disk are connected by means of reamed hole bolts and hexagonal nuts. The reamed hole bolts serve both as a connection and a fixing function and as a positioning pin for transmitting torque, and the structure is simple and reliable. A tongue and groove structure is provided between the turbine housing and the fuel pump housing, and a graphite sealing gasket is installed for compression and sealing, which has the advantages of easy installation and reliable sealing.

[0041] The above is only a specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can easily think of various equivalent modifications or replacements within the technical scope disclosed by the present invention, and these modifications or replacements should be included in the protection scope of the present invention. Therefore, the protection scope of the present invention shall be based on the protection scope of the claims.

Claims

1. A turbine, characterized in that: It includes a turbine housing, a turbine disk, a guide ring and a turbine outlet pipe; The turbine outlet pipe is fixed to the turbine housing, and the turbine housing and the turbine outlet pipe are provided with a tongue-and-groove structure for radial positioning; The guide ring is located in the turbine outlet pipe and fixed on the turbine housing; an outer stop for radial positioning is provided between the guide ring and the turbine housing; The turbine disc is located in the guide ring, and the inner side of the guide ring is provided with a labyrinth sealing groove corresponding to the turbine disc.

2. The turbine according to claim 1, characterized in that The outer edge of the turbine disc is provided with primary blades and secondary blades in the radial direction; the inner side of the guide ring is provided with primary blade labyrinth sealing grooves and secondary blade labyrinth sealing grooves corresponding to the primary blades and secondary blades respectively.

3. The turbine according to claim 1, characterized in that A sealing gasket is arranged in the tongue and groove structure.

4. The turbine according to claim 3, characterized in that The depth of the tongue and groove structure exceeds 7 mm.

5. The turbine according to claim 1, characterized in that The turbine outlet pipe and guide ring are both installed and fixed on the turbine housing through detachable parts.

6. The turbine according to claim 1, characterized in that The turbine housing is provided with an air collecting ring and a nozzle ring, and the nozzle ring is circumferentially arranged around the air collecting ring.

7. The turbine according to claim 1, characterized in that The guide ring is composed of three parts spliced ​​together.

8. A liquid rocket engine turbo pump, characterized in that: comprising a pump shaft, a fuel pump housing and a turbine as claimed in any one of claims 1 to 7; The turbine housing is fixedly connected to the fuel pump housing; the pump shaft is fixedly connected to the turbine disk, and the turbine disk can drive the pump shaft to rotate.

9. The liquid rocket engine turbopump according to claim 8, characterized in that: The pump shaft is connected to the turbine disc via a detachable part, and an inner hole is provided at the end of the pump shaft, a boss corresponding to the inner hole is provided on the turbine disc, and the inner hole and the boss are connected by interference fit.

10. The liquid rocket engine turbo pump according to claim 8, characterized in that: The turbine housing and the fuel pump housing are fixedly connected via a detachable part, and the turbine housing and the fuel pump housing are provided with a tongue and groove structure for radial positioning.

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