Turbine and applied liquid rocket engine turbine pump

Abstract

The utility model discloses a turbine and a liquid rocket engine turbine pump applying the turbine, and relates to the technical field of liquid rocket engine turbine pumps. 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. The turbine, the guide ring and the turbine shell are positioned through the outer seam allowance, 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 utility model relates to the technical field of liquid rocket engine turbopumps, in particular to a turbine and a liquid rocket engine turbopump applying the same. Background Art

[0002] The turbine of a turbopump is a structural component that provides rotational power for the turbopump. At present, most turbines of turbopumps are connected to the turbine shaft by spline connection or pin connection. The guide ring is positioned by an inner stop, and no sealing structure is provided for the guide ring. The turbine outlet pipe is welded to the turbine housing. The above structures have disadvantages such as low reliability, complex assembly process, large leakage of turbine gas, and difficult maintenance. Summary of the Utility Model

[0003] In view of the above problems, the utility model develops a turbine for a liquid rocket engine turbopump, which can avoid the above disadvantages while achieving the same functions.

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

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

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

[0007] The guide ring is located inside 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 disk is located inside the guide ring, and a labyrinth seal groove corresponding to the turbine disk is provided on the inner side of the guide ring.

[0009] Preferably, primary blades and secondary blades are provided along the radial direction on the outer edge of the turbine disk; primary blade labyrinth seal grooves and secondary blade labyrinth seal grooves corresponding to the primary blades and the secondary blades respectively are provided on the inner side of the guide ring.

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

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

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

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

[0014] The present utility model further provides a turbopump for a liquid rocket engine, which comprises 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 and the turbine disk are connected by a detachable member, and an inner hole is provided at the end of the pump shaft, a shoulder corresponding to the inner hole is provided on the turbine disk, and the inner hole and the shoulder are connected by interference fit.

[0017] Furthermore, the turbine housing and the fuel pump housing are fixedly connected by a detachable member, and a tenon groove structure for radial positioning is provided between the turbine housing and the fuel pump housing. Preferably, a gasket is provided in the tenon groove structure of the turbine housing and the fuel pump housing.

[0018] For the turbine of the present utility model, a tenon groove structure for radial positioning is provided between the turbine housing and the turbine outlet pipe, an outer stop is provided between the guide ring and the turbine housing for radial positioning, a labyrinth seal 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 tenon groove structure, which is convenient for installation and disassembly. Moreover, the labyrinth seal groove structure provided on the guide ring can reduce the leakage amount of high-temperature gas and improve the turbine efficiency. Description of the Drawings

[0019] In order to more clearly illustrate the technical solutions of the embodiments of the present utility model, the drawings required for the description of the embodiments will be briefly introduced below. Obviously, the drawings in the following description are some embodiments of the present utility model. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

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

[0021] Figure 2 It is a structural diagram of the turbine housing according to the embodiment of the present utility model.

[0022] Figure 3 It is a structural diagram of the turbine disk according to the embodiment of the present utility model.

[0023] Figure 4 It is a structural diagram of the guide ring according to the embodiment of the present utility model.

[0024] Description 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 seam; 54 - tenon groove; 55 - outer stop; 511 - turbine gas inlet; 101 - first-stage blade; 102 - second-stage blade; 103 - shoulder; 91 - first-stage blade labyrinth seal groove; 92 - second-stage blade labyrinth seal groove; 93 - first component; 94 - second component; 95 - third component; 96 - cutting seam. Detailed implementation

[0025] Next, the technical solutions in the embodiments of the present utility model will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present utility model. Obviously, the described embodiments are part of the embodiments of the present utility model, rather than all of the embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present utility model.

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

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

[0028] It should be further understood that the term " / and / " used in this specification of the present utility model and the appended claims refers to any combination and all possible combinations of one or more of the related listed items, and includes these combinations.

[0029] Please refer to Figures 1-4 the shown liquid rocket engine turbine pump, which includes a pump shaft 1, a fuel pump housing 2, and a turbine.

[0030] The turbine includes 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 to the turbine housing 5, and the turbine housing 5 and the turbine outlet pipe 13 are provided with a tenon and groove structure for radial positioning. Specifically, the turbine outlet pipe 13 is installed and fixed to the turbine housing 5 through a detachable member. In this embodiment, the detachable member is a plurality of second bolts 7, and the second bolts 7 are preferably hexagon head bolts, that is, the turbine outlet pipe 13 is installed and fixed to the turbine housing 5 through a plurality of hexagon head bolts. In this embodiment, the tenon and groove structure provided on the turbine housing 5 and the turbine outlet pipe 13 includes a tenon groove 54 provided on the turbine housing 5 and a tenon provided on the turbine outlet pipe 13 corresponding to the tenon groove 54. The quick positioning and installation of the turbine housing 5 and the turbine outlet pipe 13 can be realized through the matching of the tenon groove 54 and the tenon; a second gasket 6 is further provided in the tenon groove 54, and the second gasket 6 is preferably a graphite gasket, which is used for pressing and sealing the tenon and groove structure; in practical applications, the depth of the tenon groove 54 is preferably more than 7 mm. It can be understood that in some other embodiments, the tenon groove can be provided on the turbine outlet pipe 13, and the tenon corresponding to the tenon groove is provided on the turbine housing 5.

[0032] The guide ring 9 is located inside the turbine outlet pipe 13 and is fixed to 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 installed and fixed to the turbine housing 5 through a detachable member. In this embodiment, the detachable member is a plurality of third bolts 8, and the third bolts 8 are preferably socket head cap screws, that is, the guide ring 9 is installed and fixed to the turbine housing 5 through a plurality of socket head cap screws. In this embodiment, the outer stop 55 is provided on the turbine housing 5, and the guide ring 9 is provided with an abutting portion matching the outer stop 55. The quick positioning and installation of the turbine housing 5 and the guide ring 9 can be realized through the matching of the outer stop 55 and the abutting portion. It can be understood that in some other embodiments, the outer stop 55 can be provided on the guide ring 9, and the abutting portion matching the outer stop 55 is provided on the turbine housing 5.

[0033] In this embodiment, the guide ring 9 is composed of a plurality of components spliced together. Specifically, the guide ring 9 is integrally machined and then divided into three components by wire cutting. As Figure 4 shown, the guide ring 9 is composed of a first component 93, a second component 94, and a third component 95 spliced together. 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 beneficial to the installation and disassembly of the guide ring 9, and the installation of the guide ring 9 can be realized after the turbine rotor is installed in place.

[0034] The turbine disk 10 is located inside the guide ring 9, and a labyrinth seal groove corresponding to the turbine disk 10 is provided on the inner side of the guide ring 9. Specifically, as Figure 3The shown turbine disk 10 is a single-disk two-stage turbine disk. The outer edge is provided with first-stage blades 101 and second-stage blades 102 along the radial direction. The two-stage blades help improve the turbine efficiency. Inside the guide ring 9, there are first-stage blade labyrinth seal grooves 91 and second-stage blade labyrinth seal grooves 92 corresponding to the first-stage blades 101 and the second-stage blades 102 respectively. The labyrinth seal groove structure can reduce the leakage of high-temperature gas and improve the turbine efficiency.

[0035] The end of the pump shaft 1 extends into the turbine and is fixedly connected to the turbine disk 10. The turbine disk 10 can drive the pump shaft 1 to rotate. Specifically, the pump shaft 1 and the turbine disk 10 are connected by a detachable component. In this embodiment, the detachable component is a plurality of fourth bolts 11 and nuts 12. The fourth bolts 11 are preferably precision reamed bolts, and the nuts 12 are preferably hex nuts. That is, the pump shaft 1 and the turbine disk 10 are connected and fixed by a plurality of precision reamed bolts and hex nuts. The precision reamed bolts not only play a role in connecting and fixing but also act as positioning pins for torque transmission. The structure is simple and reliable. In some other embodiments, the hex nut and the head of the precision reamed bolt can be spot-welded and locked to prevent loosening.

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

[0037] Furthermore, as Figure 2 shown, a gas collecting ring 51 and a nozzle ring 52 are arranged on the turbine housing 5. The nozzle ring 52 is arranged circumferentially around the gas collecting ring. The gas collecting ring 51 is provided with a turbine gas inlet 511. Preferably, the gas collecting ring 51 and the nozzle ring 52 are welded by argon arc welding and then machined to form a weld seam 53 on the turbine housing. After machining and forming, it is the turbine housing 5.

[0038] The turbine housing 5 is fixedly connected to the fuel pump housing 2. Specifically, the turbine housing 5 and the fuel pump housing 2 are fixedly connected by a detachable component. In this embodiment, the detachable component is a plurality of first bolts 3. The first bolts 3 are preferably hex head bolts. That is, the turbine housing 5 is installed and fixed on the fuel pump housing 2 by a plurality of hex head bolts. In addition, the turbine housing 5 and the fuel pump housing 2 are provided with a tenon groove structure for radial positioning. The tenon groove structure includes a tenon groove provided on the fuel pump housing 2 and a tenon provided on the turbine housing 5 corresponding to the tenon groove. The quick positioning and installation of the turbine housing 5 and the fuel pump housing 2 can be realized through the matching of the tenon groove and the tenon. A first gasket 4 is also arranged in the tenon groove. The first gasket 4 is preferably a graphite gasket and is used for the compression seal of the tenon groove structure.

[0039] For the turbine of the turbopump of the liquid rocket engine of the present utility model, dovetail groove structures for radial positioning are provided on the turbine, the turbine housing and the turbine outlet pipe. An outer stop is provided between the guide ring and the turbine housing for radial positioning. A labyrinth seal 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 dovetail groove structure, which is convenient for installation and disassembly. In addition, the labyrinth seal groove structure provided on the guide ring can reduce the leakage of high-temperature gas and improve the turbine efficiency. Furthermore, the guide ring is integrally machined and then divided into three segments by wire cutting, and is positioned by the outer stop, which is convenient for installation and disassembly of the guide ring; the turbine outlet pipe is installed and fixed on the turbine housing by hexagon head bolts. A dovetail groove structure is provided between the turbine housing and the turbine outlet pipe, and a graphite gasket is installed for compression sealing. This structure has the advantages of convenient installation, reliable sealing, and reusable parts.

[0040] For the turbopump of the liquid rocket engine applying this turbine, the pump shaft and the turbine disk are connected by precision reamed bolts and hexagon nuts. The precision reamed bolts not only play a role in connection and fixation but also play a role in torque transmission as a locating pin, and the structure is simple and reliable; a dovetail groove structure is provided between the turbine housing and the fuel pump housing, and a graphite gasket is installed for compression sealing, which has the advantages of convenient installation and reliable sealing.

[0041] As mentioned above, it is only the specific implementation manner of the present utility model, but the protection scope of the present utility model is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present utility model can easily think of various equivalent modifications or substitutions, and these modifications or substitutions should all be covered within the protection scope of the present utility model. Therefore, the protection scope of the present utility model shall be subject to 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 said turbine outlet pipe is fixed on the turbine housing, and the turbine housing and the turbine outlet pipe are provided with a tenon groove structure for radial positioning; The said guide ring is located inside the turbine outlet pipe and is fixed on the turbine housing; an outer stop is provided between the said guide ring and the turbine housing for radial positioning; The said turbine disk is located inside the guide ring, and a labyrinth seal groove corresponding to the turbine disk is provided on the inner side of the guide ring.

2. The turbine according to claim 1, wherein The outer edge of the said turbine disk is provided with first-stage blades and second-stage blades along the radial direction; first-stage blade labyrinth seal grooves and second-stage blade labyrinth seal grooves corresponding to the first-stage blades and the second-stage blades respectively are provided on the inner side of the guide ring.

3. The turbine according to claim 1, characterized in that, A gasket is provided in the said tenon groove structure.

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

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

6. The turbine according to claim 1, wherein A gas collecting ring and a nozzle ring are provided on the said turbine housing, and the nozzle ring is arranged circumferentially around the gas collecting ring.

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

8. A liquid rocket engine turbopump, characterized in that, It includes a pump shaft, a fuel pump housing and a turbine as described in any one of claims 1-7; The turbine housing is fixedly connected to the fuel pump housing; the said pump shaft is fixedly connected to the turbine disk, and the turbine disk can drive the pump shaft to rotate.

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

10. The liquid rocket engine turbopump according to claim 8, wherein, The said turbine housing and the fuel pump housing are fixedly connected through a detachable part, and a tenon groove structure for radial positioning is provided between the turbine housing and the fuel pump housing.

Images