TURBOCHARGER WITH DUAL-BLADE NOZZLE SYSTEM

TURBOCOMPRESSEUR DOTE D'UN SYSTEME DE BUSE A DOUBLE PALE

English Abstract

A turbo with double-vane nozzle ring including three housings, two wheels,
fixed and straight-moving
nozzle rings The fixed nozzle ring with a set of fixed vanes which is driven
by gears and goes
straightly through the vane-shaped holes The fixed and straightly moving
adjustable nozzle rings are
set in the turbine housing passageway in order to change the passage sectional
areas The inlet air
flow is aired after designs which will broaden the turbocharger high-
efficiency zone

French Abstract

La présente invention concerne un turbocompresseur doté d'un système de buse à double pale comprenant un logement de turbine, un anneau de buse fixe (1), un disque de buse à déplacement linéaire (2), un logement intermédiaire (5), une crémaillère (4), des tiges de culbuteur (3) et un engrenage (6), des pales fixes à profil aérodynamique (8) étant disposées sur la face d'extrémité avant de l'anneau de buse fixe (1), des trous à pales (9) étant disposés entre les pales fixes (8) et l'anneau de buse fixe (1) étant revêtu sur l'extérieur du logement intermédiaire (5) et fixé sur le logement intermédiaire (5) au moyen de vis ; le disque de buse à déplacement linéaire (2) est disposé sur l'extrémité arrière de l'anneau de buse fixe (1), un groupe de pales mobiles (7) est disposé sur la face d'extrémité avant du disque de buse à déplacement linéaire (2), les pales mobiles (7) sont insérées de manière mobile dans les trous à pales (9), la face d'extrémité arrière du disque de buse à déplacement linéaire (2) est raccordée de manière fixe à deux tiges de culbuteur (3), les tiges de culbuteur (3) étant insérées dans le logement intermédiaire (5) et mises en prise avec la crémaillère (4) par le biais de l'engrenage (6). La fourniture d'une pale supplémentaire le long d'un passage d'écoulement de buse dans le turbocompresseur doté du système de buse à double pale permet non seulement de réduire la zone de section transversale du passage, mais également de séparer la buse d'origine en deux passages de gaz afin de réduire la perte d'écoulement de gaz en raison d'un écoulement transversal ; de plus, l'écoulement de gaz peut s'écouler selon un angle d'écoulement de gaz optimal selon la conception originale, de sorte que la turbine puisse continuer de fonctionner dans la plage à haut rendement.

Claims

Claims
1. A turbocharger with a double-vane nozzle system, comprising a turbine
housing, characterized
in that it further includes a fixed nozzle ring, a linearly moving nozzle
disk, a middle-housing, a
rack, a gear and rocker arm rods,
wherein a group of airfoil fixed vanes are provided on the front end face of
the fixed nozzle ring,
with blade-shaped holes arranged between the fixed vanes, the fixed nozzle
ring is provided with
a center hole at the center, and sheathed around the circumference of the
middle-housing and
fixed to the middle-housing via screws, the linearly moving nozzle disk is
mounted to the rear
end of the fixed nozzle ring, a group of moving blades is provided on the
front end face of the
linearly moving nozzle disk, and the shape of the moving blade is consistent
with that of the
blade-shaped hole, the moving blades are movably inserted into the blade-
shaped holes, the
linearly moving nozzle disk is provided with a center hole at its center and
sheathed around the
circumference of the middle-housing, the rear end face of the linearly moving
nozzle disk is
fixedly connected with two rocker arm rods, the rocker arm rods are inserted
into the
middle-housing, each of the rocker arm rods is provided with teeth at one end
and engaged with
a rack via the gear, the rack is connected to a driving device.
2. The turbocharger with a double-vane nozzle system according to claim 1,
which is
characterized in that an intake angle of the blade and the vanes is ranged
from about 18 to 24
degrees.
3. The turbocharger with a double-vane nozzle system according to claim 1,
which is
characterized in that 4 to 11 fixed vanes may be employed and 4 to 11 moving
blades may be
employed.
4. The turbocharger with a double-vane nozzle system according to claim 1,
which is
characterized in that the driving device connected to the rack is an air
packet executor or a
solenoid valve.
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Description

CA 02833790 2015-12-07
Turbocharger with Dual-Blade Nozzle System
Field of Technology
The present invention relates to a turbocharger with a double-vane nozzle
system, belonging to the field of
an automobile device.
Background Technology
Waste gas discharged from an engine can work for the turbine in the
supercharger, but it only
operates in a small high-efficiency zone. Even through the design point of the
vehicular
supercharger is set within a range of 50-70%, the over-speed of the
supercharger have to be
caused when the engine is operating at full load. Therefore, an exhaust bypass
valve mechanism
is arranged on the supercharger in order to improve the reliability while a
portion of available
energy of gas is dissipated.
An effective method to improve the aerodynamic performance of the turbine is
to employ a
variable nozzle structure, and it is also generally acknowledged and practiced
by each of the
world-wide supercharger manufacturers; at present, there are three different
solutions:
The Chinese patent application No. 200710152744.5 filed by HONEYWELL
INTERNATIONAL INC, entitled "Vane assembly and method of assembling a vane
assembly
for a variable-nozzle turbocharger" discloses a method for varying the nozzle
geometry by
changing the vane angle. Such method has an advantages that the cross-section
area of nozzle is
decreased with the decreasing of the vane angle, the reduction ratio of the
cross-section area of
nozzle may be up to 50% above; the method has the following shortcomings that
the nozzle
angle alpha ( a ) is oversized (starting state), airflow C"r attacks the
convex face of the
turbine blade; the nozzle angle alpha ( a ) is too small (full load state),
the airflow C`r attacks
the concave face of the blade (see figure 11), so that the heat efficiency of
the supercharger is
reduced regardless of operating at low or high working conditions.
The Chinese patent application No. 00819834.9 filed by HONEYWELL GARRETT SA,
entitled
"VARIABLE GEOMETRY TURBOCHARGER WITH SLIDING PISTON" discloses a simple
variable geometry mechanism, wherein the nozzle is composed of a fixing blade
and a blade-free
air passage. Only the cross-section area of the blade-free air passage is
adjustable, certainly, the
adjustable cross-section area of 50% is enough, but the aerodynamic
performance is not good.
When the blade-free passage is opened, the airflow will pass through both the
blade passage and

CA 02833790 2015-12-07
the blade-free passage at the same time, because the angle of flow of the two
passages is
different, the airflow passed the nozzle will be turbulent, and the flow
losses of the airflow is
increased, and the heat efficiency of the turbine is reduced.
According to a variable nozzle structure developed by British HOLSET Power
Engineering
Company, a shielding ring is mounted on the fixing nozzle blades, a part of
the flow path of the
nozzle can be shielded by moving the shielding ring so as to achieve the
adjustment of the cross-
section area of the nozzle. Just like the second solution, its shortcomings
are shown as that the
airflow passing from the volute to the nozzle inlet is turbulent due to
shielding the part of the
flow path of the nozzle, it also make the heat efficiency of the turbine
decreasing.
SUMMARY OF THE INVENTION
Above-mentioned shortcomings are overcome by the present invention which
provides a
turbocharger with a dual-vane nozzle system. A new vane is arranged along and
within the flow
path of the nozzle, thus the section area of the passage is reduced, and the
nozzle is partitioned
into two air passages so as to reduce the cross flow losses of the airflow.
Meanwhile, the airflow
flows at the originally designed optimum angle of flow, so as to keep the
turbine operating in the
high-efficiency zone.
In order to solve above-mentioned technical problems, the present invention
provides a technical
solution as follows:
A turbocharger with a double-vane nozzle system, comprising a turbine housing,
a fixed nozzle
ring, a linearly moving nozzle disk, a middle-housing, a rack, rocker arm
rods, and a gear,
wherein a group of airfoil fixed vanes are provided on the front end face of
the fixed nozzle ring,
with blade-shaped holes arranged between the fixed vanes, the fixed nozzle
ring is provided with
a center hole at the center, and sheathed around the circumference of the
middle-housing and
fixed to the middle-housing via screws, the linearly moving nozzle disk is
mounted to the rear
end of the fixed nozzle ring, a group of moving blades is provided on the
front end face of the
linearly moving nozzle disk, and the shape of the moving blade is consistent
with that of the
blade-shaped hole, the moving blades are movably inserted into the blade-
shaped holes, the
linearly moving nozzle disk is provided with a center hole at its center and
sheathed around the
circumference of the middle-housing, the rear end face of the linearly moving
nozzle disk is
fixedly connected with two rocker arm rods, the rocker arm rods are inserted
into the middle-
housing, each of the rocker arm rods is provided with teeth at one end and
engaged with a rack
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CA 02833790 2015-12-07
via the gear, the rack is connected to a driving device.
Furthermore, the intake angle of the blade is ranged from about 18 to 24
degrees.
Furthermore, 4 to 11 fixed vanes may be employed and 4 to 11 moving blades may
be employed
also.
Furthermore, the driving device connected to the rack is an air packet
executor or a solenoid
valve.
The turbocharger with a dual-vane nozzle system according to the present
invention is provided
with new blades along the flow path of the nozzle, so as to reduce the section
area of the passage
and partition the original nozzle into two air passages, so that the cross
flow losses is reduced.
Meanwhile, the airflow flows at the originally designed optimum angle of flow,
and the turbine
operate in the high-efficiency zone. The moving blades and the fixed vanes are
arranged in a
streamwise direction, thereby avoiding the turbulence caused by the second
solution and the third
solution, reducing the flow resistance losses. By increasing or decreasing the
number of the
blades, the area of the nozzle outlet can be regulated. When the moving blades
insert into the
fixed vanes completely, the reduction ratio of the section area of the flow
path can be adjusted by
the thickness of the blade, so that the demands of the variable working
condition of the engine
can be satisfied. Depend on the actual demands, the thickness of blade is
different in different
turbochargers.
BRIEF DESCRIPTION OF THE DRAWINGS
The accompanying drawings are used for understanding the present invention
better and form a
part of the description, which explain the present invention with the
embodiments and is not
intended to limit the scope of the present invention. Wherein:
Figure 1 is a schematic diagram of the structure of the turbocharger with a
dual-vane nozzle
system according to the present invention;
Figure 2 is a schematic diagram of the structure of the linearly moving nozzle
disk according to
the present invention;
Figure 3 is a schematic diagram of the structure of the fixed nozzle ring
according to the present
invention;
Figure 4 is a schematic side view of the fixed nozzle ring according to the
present invention;
Figure 5 is a schematic diagram of the assembly of the linearly moving disk
and the rocker arm
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rods according to the present invention;
Figure 6 is a schematic diagram of the structure of the rocker arm rod
according to the present
invention;
Figure 7 is a schematic diagram of the structure of the rack according to the
present invention;
Figure 8 is a schematic side view of the structure of the gear according to
the present invention;
Figure 9 is a schematic front view of the structure of the gear according to
the present invention;
Figure 10 is a schematic diagram of the assembly of the linearly moving nozzle
disk, the fixed
nozzle ring and the rocker arm rods according to the present invention;
Figure 11 is a schematic diagram of the technical analysis of the first
solution in the Background.
DETAILED DESCRIPTION
The preferred embodiments of the invention will be described by taking in
conjunction with the
accompanying drawings, it should be understood that the preferred embodiments
illustrated
herein is only intended to illustrate and explain the present invention rather
than limiting the
scope of the present invention.
Embodiment I
Figures 2, 3 and 10 show 16 vanes and 16 moving blades, however, in Embodiment
I, it is given
that there are eight fixed vanes 8 and eight moving blades 7, and the intake
angle of the blade, i.e.
the blade incidence is 21 degrees.
Shown as Figures 1, 4, and 10, a group of airfoil fixed vane 8 are provided on
the front end face
of the fixed nozzle ring 1, blade-shaped holes 9 are arranged between the
fixed vanes 8, the fixed
nozzle ring 1 is provided with a center hole at the center and sheathed around
the circumference
of the middle-housing 5 and fixed to the middle-housing 5 via screws, a
linearly moving nozzle
disk 2 is mounted on the rear end of the fixed nozzle ring 1.
Shown as Figures 2 and 10, a group of moving blades 7 are provided on the
front end face of the
linearly moving nozzle disk 2, shape of the moving blade 7 is consistent with
that of the blade-
shaped hole 9, the moving blades 7 are moveably inserted into the blade-shaped
holes 9.
Shown as Figures 1, 5, 6, and 10, two rocker arm rods 3 are fixed to the rear
end face of the
linearly moving nozzle disk 2 via screws, the moving blade 7 on the front end
face of the linearly
moving nozzle disk 2 are inserted into the blade-shaped holes 9 in the fixed
nozzle ring 1, the
fixed nozzle ring 1 and the linearly moving nozzle disk 2 are sheathed around
the circumference
of the middle-housing 5, and two rocker arm rods 3 are inserted into
corresponding openings in
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the middle-housing 5, the openings in the middle-housing are located at the
edge of an oil
scavenge cavity of the middle-housing 5 and free from interference with the
oil scavenge in the
middle-housing 5. Teeth are provided on the end of the rocker arm rods 3 which
engage with a
rack 4 via a gear 6.
Shown as Figures 1 and 3, the fixed nozzle ring 1 are provided with four round
holes in the
central part thereof which aligned with the threaded holes in the middle-
housing 5, and fixedly
connected to the middle-housing 5 by tightening screws. After debugging, it is
required that the
moving blades 7 be able to slide within the blade-shaped holes 9 in the fixed
nozzle ring 1
smoothly.
With respect to the range of the movement of the moving blades 7, the maximum
position is
flushed with the front end of the fixed vane 8 while the minimum position is
flushed with the
rear end face of the fixed nozzle ring 1.
Shown as Figures 6, 7, 8, and 9, both ends of the rack 4 are provided with
teeth, and the end of
the rocker arm rod 3 is provided with teeth, an air packet executor pushes the
rack 4 upward and
downward, since the rack 4 is engaged with the gear 6, the gear 6 is driven to
rotate, and the gear
6 is engaged with the teeth on the end of the rocker arm rod 3, thereby the
rocker arm rod 3 is
driven leftward and rightward. The rocker arm rods 3 are fixedly connected to
the linearly
moving nozzle disk 2 through screws, thereby the linearly moving nozzle disk 2
being moved
laterally, and realizing the action of moving the moving blades 7 into or from
the blade-shaped
holes 9.
According to the demands of the variable working conditions of the engine, the
linearly moving
nozzle disk 2 is moved so that the moving blades 7 insert into the fixed
nozzle ring 1 gradually
until a complete insertion being achieved, so that the number of the vanes of
the nozzle is
increased, or the moving blades 7 are gradually retracted from the fixed
nozzle ring 1 until the
front end face of the moving blade 7 be moved to a position flushed with the
rear end face of the
fixed nozzle ring 1, so that the number of the vanes of the nozzle is
decreased. The purpose of
adjusting the outlet area of the nozzle is achieved by adjusting the number of
the vanes.
The turbocharger with a dual-vane nozzle system according to the present
invention is provided
with new blades along the flow path of the nozzle, so as to reduce the section
area of the passage
and partition the original nozzle into two air passages, so that the cross
flow losses is reduced.
Meanwhile, the airflow flows at the originally designed optimum angle of flow,
and the turbine
5

CA 02833790 2015-12-07
operate in the high-efficiency zone. The moving blades and the fixed vanes are
arranged in a
streamwise direction, thereby avoiding the turbulence caused by the second
solution and the third
solution, reducing the flow resistance losses. By increasing or decreasing the
number of the
blades, the area of the nozzle outlet can be regulated. When the moving blades
insert into the
fixed vanes completely, the reduction ratio of the section area of the flow
path can be adjusted by
the thickness of the blade, so that the demands of the variable working
conditions of the engine
can be satisfied. Depend on the actual demands, the thickness of blade is
different in different
turbochargers.
Embodiment II
The difference between the present embodiment II and the embodiment I is that
the driving
device pushing the rack upward and downward is a solenoid valve.
At last, it shall be noted that the above description is the preferred
embodiments of the present
invention only, it is not intended to limit the scope of the present
invention. Although the present
invention has been described in detail with respect to the above-mentioned
embodiments, the
technical solution disclosed in the embodiments described above can be
modified by the skilled
person in the art, or equal substitution of some technical features can be
made.
6

Representative Drawing