Device for separation of the pump and the turbine of the booster turbo-pump aggregate of the liquid propellant rocket engine

FIELD: rocket engineering; production of the devices for the liquid propellant rocket engines.

SUBSTANCE: the invention is pertaining to the field of rocket engineering and may be used in the liquid propellant rocket engines (LPRE). The device for separation of the pump and the turbine of the booster turbo-pump aggregate of the LPRE consists of the pump (2), the turbine (3), the separating cavity (1) located between the pump (2) and the turbine (3) and the external intake tract (4). The separating cavity (1) is limited from the side of the pump (2) by the shaft gasket (5), which diameter is made smaller than the diameter of the shaft (10) in the area of the seat of the bearing of the turbine (11), and from the side of the turbine (3) - by the unloading disk (6) aligned with the turbine impeller (7). On the turbine impeller (7) there is the gasket of the unloading disk (8). The axial impeller of the pump (9) and the turbine impeller (7) are fixed on the shaft (10). From the direction of the turbine (3) the shaft (10) rests on the turbine bearing (11), which is brought out beyond the bounds of the separating cavity (1) and is installed from the direction of the pump (2). The cavity of the turbine bearing (12) which is adjoining the shaft gasket (5) is connected by the delivery channels (13) with the pump outlet (14). The offered device ensures the minimum losses of the power used for separation of the pump and the turbine, and also the effective refrigeration of the bearings by the liquid monophase hydrogen.

EFFECT: the invention ensures the minimum losses of the power used for separation of the pump and the turbine, the effective refrigeration of the bearings by the liquid monophase hydrogen.

2 cl, 2 dwg

 

The invention relates to the field of rocketry and can be used in liquid rocket engines (LRE).

In LPRE widely used booster turbopump units with axial pump, the drive for which is a gas turbine. Such booster turbopump units due to the simplicity of design of the axial pump is designed for high reliability.

It is known a device for separating the pump and turbine hydrogen booster turbopump Assembly LRE containing dividing the cavity between the pump and the turbine, limited by pump shaft seals, and wheel side of the turbine discharge CD with his seal. In the separation cavity working environment is supplied from an external source. In the separation cavity between the shaft seal and unloading a disk placed the turbine bearing.

(Cosmonautics and rocket engineering, vol. 16. TsNIIMash, 1999. P.79. Figure 6 - prototype).

This booster turbopump Assembly has the following disadvantages.

When working booster turbopump Assembly with axial pump on its axis, the wheel operates the axial force generated due to them by the pressure differential. This axial force acts in the direction from the outlet to the inlet of the pump. The higher the pressure differential created by the pump, the greater the magnitude of the axial forces acting yasevoe wheel pump. The magnitude of this force can be several thousand kilonewton. As booster pumps, turbines are used with low pressure drop on the impeller, the axial force acting on the rotor of the turbine is small and can't balance the axial force from the axial wheel pump. Therefore, to balance axial forces from the axial wheel pump set should be used in the separation cavity unloading a disc of large diameter. In the known device the diameter of the shaft seal is larger than the diameter of the shaft in place in the bearing of the turbine, which also entails an increase in the diameter of the discharge disk. The increased diameter of the discharge drive leads to increased power losses associated with the rotation of the disk. In addition, the increased diameter of the shaft seals and unloading of the disk cause increased power losses associated with leakage of the working medium from the separation cavity. In booster turbopump units rocket engine of small thrust reducing leakage from dividing the cavity into the cavity of the turbine is especially important, since these leakage value can be comparable to the expense of the working gas through the turbine.

In the separation chamber between the pump and turbine of the specified device is fed to the high pressure hydrogen from the hydrogen output of the main pump is urbanzone unit. This hydrogen is in the gas phase, which worsen the conditions of cooling of the bearing of the turbine.

The task of the invention is to eliminate these drawbacks of the separation of pump and turbine booster turbopump Assembly LRE by reducing power loss required for separation of the pump and turbine, and improve cooling of the bearing of the turbine.

This object is achieved in that the device separation of the pump and turbine booster turbopump Assembly LRE containing a pump, a turbine, dividing the cavity between the pump and the turbine, limited by pump shaft seals, and from the side of the turbine discharge CD with his seal, executed tract external supply of working medium in the separation cavity and the bearing of the turbine, according to the invention unloading a CD with his seal combined with a turbine wheel, the diameter of the shaft seal is made smaller than the diameter of the shaft in place in the bearing of the turbine, and the turbine bearing is installed with hand pump outside the separation cavity.

To improve cooling of the turbine bearing its cavity, adjacent to the separation cavity, reported the inlet channels from the outlet of the pump.

The proposed device separate pump and turbine booster curb the pump unit LRE presents drawings:

figure 1 is a longitudinal section of a hydrogen booster turbopump unit with a device for separating the pump and turbine;

figure 2 - element separation devices of the pump and the turbine, where

1 - the separation cavity,

2 - pump,

3 - turbine

4 - the path of the external supply,

5 - shaft seal,

6 handling the drive,

7 - turbine wheel,

8 - seal unloading disk

9 - axis of the pump impeller,

10 - Val,

11 - bearing turbine,

12 - the bearing of the turbine,

13 - supplying channels

14 - output pump.

The device consists of dividing the cavity 1 between the pump 2 and the turbine 3 and tract external supply 4. Dividing the cavity 1 is limited by pump 2 seal shaft 5, the diameter of which is smaller than the diameter of the shaft in place in the bearing of the turbine, and the turbine 3 is limited to the discharge disc 6, combined with the turbine wheel 7. On the turbine wheel 7 compacted unloading of the disk 8. Axial pump impeller 9 and the turbine wheel 7 mounted on the shaft 10. Of the turbine shaft 3 10 rests on the bearing of the turbine 11, located at the side of the pump beyond the separation cavity. The bearing of the turbine 12, adjacent to the shaft seal 5, reported the inlet channels 13 with the outlet of the pump 14.

When working booster turbopump unit section is sustained fashion cavity 1 through the path of the external supply 4 is fed to the high pressure hydrogen from an external source, for example, the output of the main pump turbopump Assembly LRE. The hydrogen pressure in the separation cavity 1 exceeds the pressure in the cavities of the pump 2 and the turbine 3. This eliminates the leakage of hydrogen gas from the turbine 3 in the cavity of the pump 2. From the separation cavity 1 hydrogen leaked into the cavity of the turbine 3 through the seal unloading of the disk 8, and the pump cavity 2 through the shaft seal 5.

When working on the axial wheel pump 9 is effective axial force is created acting on it by the pressure differential. This effort is directed away from the outlet to the inlet of the pump. As the turbine wheel 7 is practically no pressure drop, it applies an axial force directed in the same direction as the axial force acting on the axial wheel pump 9. Axial forces acting on the turbine wheel 7 and the axial wheel pump 9, the balanced axial force acting on the discharge disc 6 and directed in the opposite direction, i.e. from input to output of the pump. As the discharge disc 6 is combined with the turbine wheel 7, the power loss by friction unloading of the disk 6 and the turbine wheel 7 on the environment is minimal.

Unlike the prototype, where the diameter of the seal is larger than the diameter of the shaft in place in the bearing of the turbine, the shaft seal 5 is located on the diameter, the smaller diameter of the shaft 10 in place bearing Urbina 11. This ensured the reduction of power losses due to the reduction of leakage through the shaft seal 5.

The area of the discharge disc 6 is determined by the amount of axial force required to balance the axial forces acting on the turbine wheel 7 and the axial wheel pump 9. When a given area of the discharge disc 6 reduction of the diameter of the shaft seal 5 leads to the reduction of the diameter of the seal unloading of the disk 8. This is achieved by reducing power losses by reducing leakage through the seal unloading of the disk 8.

From the output of the pump 14 through the inlet channels 13 in the bearing of the turbine 12 is fed liquid hydrogen, which is mixed with the warmer gaseous hydrogen supplied through the shaft seal 5. When mixed with liquid hydrogen, the hydrogen gas is condensed and through the bearing of the turbine 11 is hydrogen in the liquid phase, which ensures reliable cooling of the bearing. It also improves the reliability and the entire pump, as it eliminates the flow of hydrogen gas in the working chambers of the pump.

In the proposed device for separating the pump and turbine booster turbopump Assembly LRE achieve minimal power loss associated with the separation of the pump and turbine. This ensures efficient cooling of the bearings of the liquid one is phase hydrogen.

1. A device for separating the pump and turbine booster turbopump Assembly of liquid rocket engine (LRE)containing a pump, a turbine, dividing the cavity between the pump and the turbine, limited by pump shaft seals, and from the side of the turbine and unloading a CD with his seal, tract external supply in the separation cavity and the bearing of the turbine, characterized in that the discharge drive with his seal combined with a turbine wheel, the diameter of the shaft seal is made smaller than the diameter of the shaft in place in the bearing of the turbine, and the turbine bearing is installed with hand pump for the separation cavity.

2. The device according to claim 1, characterized in that the bearing of the turbine, adjacent to the separation cavity, reported the inlet channels from the outlet of the pump.



 

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EFFECT: increased reliability of turbopump set.

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