JPH0634137U - Exhaust gas turbine supercharger - Google Patents

Abstract

(57) [Abstract] [Purpose] To prevent contact accidents with the turbine impeller due to over opening of the vaned nozzle. [Structure] A plurality of vane nozzles 12 are arranged on an outer peripheral portion of a turbine impeller 4. The vaned nozzle 12 can be opened and closed through the displacement of the shaft 13 and the link 14 which penetrate the turbine shroud 9. A stopper is provided on the outer side of the turbine shroud 9. The stopper regulates the displacement of the link 14 in the nozzle opening direction.

Description

[Detailed description of the device]

[0001]

[Industrial applications]

 The present invention relates to an exhaust gas turbine supercharger capable of adjusting the flow rate of introduced gas.

[0002]

[Prior art]

An exhaust gas turbine supercharger that incorporates a plurality of vaned nozzles and adjusts the flow rate of gas introduced into the turbine by changing the throat between the vaned nozzles has been conventionally adopted. There is a configuration shown in FIGS. 3 and 4. That is, the turbine housing 1 and the compressor housing 2 are integrated with each other through the bearing housing 3, and the turbine impeller 4 in the turbine housing 1 and the compressor impeller 5 in the compressor housing 2 are connected to each other by the bearing 7 in the bearing housing 3. The turbine shaft 6 is rotatably supported, and the turbine impeller 4 is rotated by a gas flow to rotate the compressor impeller 5 so that air is sucked, compressed and discharged. Between the turbine housing main body 8 and the turbine shroud 9 attached to the inner peripheral portion of the turbine housing main body 8 on the gas outlet 20 side by the opposed annular flow path forming surfaces 11a and 11b. 11 is formed and the gas introduced from the gas inlet 19 is In the configuration in which the scroll passage 10 provided in the housing body 8 is guided to the turbine impeller 4 through the annular flow passage 11, a plurality of vane nozzles 12 are arranged in the annular flow passage 11 in the circumferential direction. Each of the vane nozzles 12 is fixed to the inner end of a shaft 13 that penetrates the turbine shroud 9, while one end of a link 14 is attached to the outer end of each shaft 13 and the other end of each link 14 is attached. The chains are connected in the circumferential direction by a chain link 15 arranged outside the turbine shroud 9, and the chain link 15 is moved in the circumferential direction via a lever 16, a shaft 17 and an arm 18 by an actuator (not shown). The opening and closing angle of each vane nozzle 12 can be changed by rotating the link 14 and the shaft 13 by Certain throat L _S between the respective Bendonozuru 12 and control child a close angle a structure in which to be able to vary the flow rate of the gas from the large flow rate to the small flow rate by widening or narrowing adjusted.

Further, in the turbine housing 1 of such an exhaust gas turbine supercharger, generally, an external stopper is provided in order to hold the opening / closing angle of each vaned nozzle 12 fixed.

[0004]

[Problems to be solved by the device]

 However, in the case of the exhaust gas turbine supercharger, since the open / close angle of the vane nozzle is fixedly held by the external stopper, for example, the distance from the external stopper or actuator to the lever 16, the shaft 17, or the arm 18 is increased. If the vane nozzle 12 cannot be held from the outside and the vaned nozzle 12 opens too much due to a failure of the power transmission mechanism of the vane nozzle 12, the tip of the vaned nozzle 12 enters the turbine impeller 4 and a contact accident occurs. May occur.

In view of the above, according to the present invention, even if a situation occurs in which the opening / closing angle of the vane nozzle cannot be fixed and maintained from the outside, a contact accident between the vane nozzle and the turbine impeller due to the excessive opening of the vane nozzle is caused. It tries to be able to prevent it.

[0006]

[Means for Solving the Problems]

 In order to solve the above problems, the present invention provides an annular flow path for guiding gas to a turbine impeller between a turbine housing body and a turbine shroud attached to an inner peripheral portion of a gas outlet side of the turbine housing body. A plurality of vane nozzles are arranged in the annular flow passage, each vane nozzle is supported at one end of a shaft that penetrates the turbine shroud, and is linked to the other end of each shaft in the circumferential direction. An exhaust gas turbine supercharger having a turbine housing in which the opening and closing angles of each vane nozzle can be adjusted by rotating the shafts in the same direction by interlocking displacement of the links. Install a stopper at the required position of the part to prevent the opening of the vane nozzle by restricting the displacement of the above link. Give composed of configuration to.

[0007]

[Action]

 When the opening / closing angle of the vaned nozzle cannot be fixed and held from the outside, and the force in the opening direction acts on the vaned nozzle, the displacement of the link in the nozzle opening direction is restricted by the stopper of the turbine shroud portion. Therefore, the vaned nozzle is prevented from opening too much, and the contact accident with the turbine impeller due to opening too much is prevented.

[0008]

【Example】

 An embodiment of the present invention will be described below with reference to the drawings.

FIGS. 1 and 2 show an embodiment of the present invention. In an exhaust gas turbine supercharger having the same structure as shown in FIGS. 3 and 4, an annular flow passage is formed in a turbine housing body 8. A surface of the nozzle ring 21 is formed as a nozzle ring 21 which is hollowed through the surface 11a in the circumferential direction to be fitted separately to the turbine housing body 8, and the surface of the nozzle ring 21 serving as the annular flow passage forming surface 11a, and the turbine shroud 9. Pipe-shaped spacers 22 for maintaining a constant gap between the annular flow passages 11 formed by the annular flow passage formation surfaces 11a and 11b are disposed at least at three circumferential positions between the annular flow passage formation surface 11b and the annular flow passage formation surface 11b. Further, the turbine shroud 9 and the nozzle ring 21 are fastened with bolts 23 at the intervening points of the respective spacers 22 to fix the nozzle ring 21 to the turbine shroud. 9, the nozzle ring 21, the spacer 22, the bolt 23, the vane nozzle 12, the shaft 13, the link 14 and the like are integrated into the turbine shroud 9 to form a turbine shroud side assembly 24. Reference numeral 25 indicates a seal ring attached to the outer peripheral portion of the nozzle ring 21 on the fitting end side.

Further, among the bolts 23 that fasten the nozzle ring 21 and the turbine shroud 9, at least one portion (bottom in the figure) of the bolt 23 has a large head portion 23 a to prevent the vane nozzle 12 from opening too much. The stopper is used as a stopper for preventing the displacement of the link 14 located in the vicinity in the nozzle opening direction by the bolt head 23a.

Due to the above-mentioned configuration, for example, a failure occurs in the external stopper or the power transmission mechanism section from the actuator to the arm 18, and the opening / closing angle of the vane nozzle 12 cannot be fixed and held from the outside. When a force in the opening direction is applied to the vane nozzle 12 in the case of occurrence of the force, the force is transmitted from the shaft 13 to the link 14 and the link 14 is also displaced in the nozzle opening direction. Of the bolts 23 that fasten the turbine shroud 9 to the turbine shroud 21, the head 23a of one bolt 23 functions as a stopper, which prevents the vane nozzle 12 from opening too much. That is, in FIG. 2, since the head portion 23a of the bolt 23 located at the lowermost portion is made larger, the link head 14 located near the bolt portion 23a comes into contact with the bolt head portion 23a as shown by a chain double-dashed line and further displacement is caused. Therefore, the other links 14 interlocking with the links 14 are similarly restricted from further displacing, whereby the opening of each vaned nozzle 12 can be suppressed and the turbine impeller 4 can be prevented. It is possible to prevent contact accidents with them.

Further, in the present invention, the portion of the annular flow passage forming surface 11 a of the turbine housing body 8 is formed as a nozzle ring 21 separate from the turbine housing body 8, and the nozzle ring 21 is provided with a spacer 22 interposed therebetween. The turbine shroud 9 is integrated with the turbine shroud 9 by means of the bolts 23 to form the turbine shroud side assembly 24. The clearance C can be set minutely. Further, since the nozzle ring 21 serves as a turbine shroud side assembly 24 and is fitted separately when the turbine shroud 9 is attached to the turbine housing main body 8, the heat of the turbine housing main body 8 is prevented. It is not affected by the deformation, and therefore, the side clearance C can be kept constant, so that there is an advantage that an optimum flow rate characteristic can always be obtained.

In the above embodiment, the portion of the annular flow passage forming surface 11a of the turbine housing body 8 is a nozzle ring 21 separate from the turbine housing body 8, and the nozzle ring 21 is integrated with the turbine shroud 9. Although the head portion 23a of the bolt 23 for making it work is used as a stopper to prevent the opening of the vane nozzle 12 too much, the nozzle ring 21 is not provided in the supercharger as shown in FIG. In this case, a special stopper may be provided on the outer side of the turbine shroud 9 to restrict the displacement of the link 14, and other various changes may be made without departing from the scope of the invention. Of course.

[0014]

[Effect of device]

 As described above, according to the exhaust gas turbine supercharger of the present invention, the stopper that restricts the displacement in the nozzle opening direction of the link that opens and closes the vane nozzle through the rotation of the shaft is provided at the required position on the outer side of the turbine shroud. Therefore, even if the opening / closing angle of the vane nozzle cannot be fixed and held by the external stopper, the displacement of the link can be regulated by the stopper to prevent the vane nozzle from opening too much. It has the excellent effect of preventing contact accidents with the turbine impeller due to over-opening, and achieving high reliability with a simple structure.

[Brief description of drawings]

FIG. 1 is a schematic view showing an embodiment of an exhaust gas turbine supercharger of the present invention.

FIG. 2 is a schematic arrow view taken along the line AA of FIG.

FIG. 3 is a schematic diagram showing an example of an exhaust gas turbine supercharger.

FIG. 4 is a schematic view taken along the line BB of FIG.

[Explanation of symbols]

 1 Turbine Housing 4 Turbine Impeller 8 Turbine Housing Main Body 9 Turbine Shroud 11 Annular Flow Path 12 Vane Nozzle 13 Shaft 14 Link 23 Bolt 23a Head (Stopper)

Claims (1)

[Scope of utility model registration request] 1. An annular flow passage is formed between a turbine housing main body and a turbine shroud mounted on an inner peripheral portion of the turbine housing main body on a gas outlet side, and an annular flow path is formed to guide gas to a turbine impeller. A plurality of vaned nozzles are arranged in a path, each of the vaned nozzles is supported at one end of a shaft that penetrates the turbine shroud, and a link is attached to the other end of each shaft so as to interlock in the circumferential direction. In an exhaust gas turbine supercharger having a turbine housing in which the opening and closing angles of the vane nozzles can be adjusted by rotating the shafts in the same direction by the interlocking displacement of the link, at the outer shell required position of the turbine shroud, A discharge mechanism characterized by being equipped with a stopper for regulating the displacement to prevent the vane nozzle from opening too much. Air-gas turbine supercharger.