CN1400399A

CN1400399A - Small-type radial-flow or mixed-flow turbo supercharger

Info

Publication number: CN1400399A
Application number: CN02136346A
Authority: CN
Inventors: 孙敏超
Original assignee: Individual
Current assignee: Individual
Priority date: 2002-08-01
Filing date: 2002-08-01
Publication date: 2003-03-05
Anticipated expiration: 2022-08-01
Also published as: CN1179136C

Abstract

The present invention discloses a turbosupercharger for automobile (car, light truck and lorry), tractor, agricultural machine and engineering machine supercharging internal combustion engine. As compared with structure of the traditional and typical small radial-flow or mixed-flow turbosupercharger said invention is characterized by that its turbine impeller is a kind of forward-curved blade vane wheel (reasonable selective range of blade inlet geometrical angle is: beta IA is greater than or equal to 45 degC or is less than or equal to 75 deg.C). Said invention can obviously raise the efficiency of the turbosupercharger.

Description

A kind of small-type radial or combined flow turbine pressurized machine

The present invention relates to the interior turbosupercharger of boosting internal combustion engine technical field that automobile (car, Light-duty Vehicle, lorry), tractor, farm machinery and engineering machinery are used.

The Vehicular internal combustion engine power condition changing is frequent, load variations big, rotating speed using scope broadness.Vehicle Turbocharged internal-combustion engine rated power is little, and air-mass flow is little, but the rated speed height.For satisfying the requirement of low rotation speed large torque, (its turbine is the radial-flow type or the mixed-flow impeller of steamboat footpath size and adopts non-blade nozzle ring, i.e. vaneless scroll for Vehicle Turbocharged internal-combustion engine adapted small-type radial or combined flow turbine pressurized machine; Compressor impeller is the semi-open type or the closed centrifugal gas compressor backward-bladed impeller of steamboat footpath size and adopts vaneless diffuser, so that obtain higher turbine efficiency and compressor efficiency in the changes in flow rate scope of broadness).

It is 90 ° Mechanical Builds that the blade shape of centripetal turbine impeller inlet in radial-flow type of the prior art or combined flow turbine pressurized machine part all adopts how much angles of blade import.When Vehicle Turbocharged internal-combustion engine during in the operation of the slow-speed of revolution, running on the lower load, the speed ratio of centripetal turbine level and rim velocity are all lower, impeller inlet relative wind angle is very little, and the impeller inlet that equals 90 ° at how much angles of blade import forms big high incidence impact loss, causes turbine efficiency significantly to reduce.In the present invention patent (ZL96229516.7 into application is proposed, " a kind of radial-flow type and mixed-flow centripetal turbine impeller ") in, a kind of General Construction that improves existing turbine wheel inlet part is disclosed, also be, how much angles of blade import that the forward curved vane turbine wheel that is acute angles with how much angles of blade import replaces prior art all to adopt are 90 ° radial blade turbine wheel, like this, when the Vehicle Turbocharged internal combustion engine in the slow-speed of revolution, during the operation of running on the lower load scope, have only and adopt how much little turbine wheels in angle of blade import just can comply with speed ratio and all lower very little characteristics in impeller inlet relative wind angle that cause of rim velocity because of the centripetal turbine level, reduce high incidence, reduce impact loss, keep high efficiency.The forward curved vane turbine wheel structure that how much angles of blade import are acute angle can satisfy these needs just.With blade import how much angles is that 90 ° radial blade turbine wheel is compared, and the forward curved vane turbine wheel has been saved the energy that impact loss that the radial blade turbine produces at the slow-speed of revolution, the big high incidence of running on the lower load expends.This part energy as effective merit of turbine, can make secondary speed increase, gas compressor boost pressure increase in the forward curved vane turbine.This will help to overcome that present Vehicular internal combustion engine ubiquitous acceleration of turbosupercharger when the slow-speed of revolution, running on the lower load operation is poor, negative pressure appears in variable working condition low-response and blower outlet shortcoming and disadvantage.When internal-combustion engine was crossed the Maximum Torque operating mode and continued the rising rotating speed again, the negative angle of attack appearred in the import meeting of turbine wheel, and it is also increasing to increase the negative angle of attack with rotating speed.Because much smaller (the bending blade shape of forward curved vane in the turbine inlet environs of impact loss that the impact loss that the negative angle of attack produces produces than high incidence, make in blade passage, turns all the same pressure side that points to blade of action direction of normal inertial force of generation of centrifugal inertia force that the impeller high speed rotating produces and inlet air flow with Coriolis inertial force, suppress effectively, retrained the expansion of flow separation on the blade pressure surface that the negative angle of attack causes, greatly reduce the impact loss that the negative angle of attack produces), therefore the impact loss that the little negative angle of attack produces is very limited, has only when the negative angle of attack increases to very big value just can produce big impact loss.This characteristic of forward curved vane turbine wheel makes turbosupercharger can keep high efficiency when Vehicular internal combustion engine slow-speed of revolution operating mode, and has certain constrain function when high rotating speed operating mode.Also promptly for the not too high Vehicular internal combustion engine of rated speed, turbosupercharger can not added the device as any regulation and control boost pressures such as exhaust gas bypass bleed valve, compressor air inlet machine prerotator and variable-angle nozzle blades when high rotating speed operating mode, move with big negative angle of attack state only according to the forward curved vane turbine wheel, just can limit the lift-rising of turbine power, reach and suppress the purpose that boost pressure excessively raises, prevent the excessive and turbocharger rotor overspeed seriously of supercharging.

Fig. 1 is how much angle β of centripetal turbine impeller blade import _1ADefinition figure.How much angle β of the blade import of centripetal turbine impeller _1ABe that 3. at the tangent line at import leading edge place 4. and the angle between the peripheral velocity negative direction 1. impeller channel geometrical center surface of revolution go up blade profile center line 2..

The present invention is the improvement of patent ZL96229516.7.In the present invention, point out how much angle β of forward curved vane impeller blade import _1ASelect relevant with following factors: the flow passage component size of forward curved vane turbine stage; The optimum Match duty parameter of Vehicle Turbocharged internal-combustion engine and turbosupercharger; The declared working condition parameter of internal-combustion engine; Blade strength.Rational β _1AValue should be able to make pressurized machine keep high efficient in internal-combustion engine slow-speed of revolution operating mode, and guarantees not occur the excessive and supercharger rotor overspeed seriously phenomenon of supercharging in high rotating speed operating mode.By suitable adjustment turbine flow passage component size and β _1AThe size of value just can satisfy above-mentioned requirements.For the small-type radial or the combined flow turbine pressurized machine of Vehicle Turbocharged internal-combustion engine adapted, how much angle β of forward curved vane turbine wheel blade import _1ARationally to select with scope be 45 °≤β _1A≤ 75 °.

Below, with accompanying drawing technology contents of the present invention is narrated explanation in conjunction with the embodiments.

Object lesson shown in Fig. 2 is how much angle β of a blade import _1AEqual the shape of 50 ° semi-open type forward curved vane mixed flow type turbine vane.

Shown in Fig. 3 is the topology view of one embodiment of the invention.

This embodiment is the small-type radial turbosupercharger.It is made up of single-stage radial-flow type forward curved vane impeller turbine, single-stage enclosed backward-bladed impeller centrifugal-flow compressor and middle case three big major components that floating bearing, thrust bearing and oil-sealing arrangement be housed.Wherein, turbine wheel 16 and centrifugal compressor impeller 3 cantilevers are installed in the rotating shaft two ends.The rotor of turbosupercharger by centrifugal compressor enclosed backward-bladed impeller 3, axle envelope 5 and spacing thrust housing 10 by linking into an integrated entity through the turbine shaft 16 and the locking nut 2 of friction welding be combined into by rotating shaft and radial-flow type forward curved vane turbine wheel.The vaneless scroll 17 of radial turbine level adopts the outlet sidewall to be skewed 360 ° of full admission pear-shaped section of single channel spiral case.The end nut 2 of calming the anger is fixed on compressor impeller 3 on the turbine shaft 16, also axle envelope 5 and spacing thrust housing 10 is compressed simultaneously.Middle case 15 upper ends have an oil inlet hole,, lubricant oil radially enters and is divided into two-way behind the middle casing: one tunnel lubrication pressure mechanism of qi end floating bearing 11 and thrust bearing 9; The turbine end floating bearing is lubricated on another road.On axle envelope 5, the twice annular groove is arranged, respectively adorn a seal ring 6 in the groove near the setting of compressor impeller end.In rotating shaft, annular groove is arranged one, two seal rings 13 that otch is staggered are housed in the groove, prevent leakage of oil and gas blowby near the turbine wheel back of the body.In the outside of thrust bearing 9 oil blocking cover 7 is arranged, block the lubricant oil that throws away and make it flow to spill port.Floating bearing 11 is contained in the middle case 15, and two ends are blocked with back-up ring 12.Wheel dorsal part at turbine wheel is equipped with thermal shield 14, prevents that gas heat quantity from importing middle case in a large number into and influencing the bearing proper functioning.The gas collection road of compressor casing 1 is snail like, and its through-flow flow channel shape is for becoming the circular section.Gas acts on epitrochanterian end thrust, acts on the thrust bearing 9 that is fixed on the middle case 15 by spacing thrust housing 10 on the axle.

Claims

A kind of small-type radial or combined flow turbine pressurized machine, it is made up of single-stage radial-flow type or combined flow turbine, single-stage semi-open type or enclosed backward-bladed impeller centrifugal compressor and middle case three parts that floating bearing, thrust bearing and oil-sealing arrangement be housed.It is characterized in that: turbine wheel is the forward curved vane impeller, how much angle β of its blade import _1ARationally to select with scope be 45 °≤β _1A≤ 75 °.