U.S. patent application number 13/120839 was filed with the patent office on 2011-10-20 for impeller for turbine.
This patent application is currently assigned to MAC CO., LTD.. Invention is credited to Hiroaki Matsushita.
Application Number | 20110255979 13/120839 |
Document ID | / |
Family ID | 41036696 |
Filed Date | 2011-10-20 |
United States Patent
Application |
20110255979 |
Kind Code |
A1 |
Matsushita; Hiroaki |
October 20, 2011 |
IMPELLER FOR TURBINE
Abstract
An impeller for a turbine includes an impeller body formed by
alternately stacking and fixing two or more types of disk blades, a
base plate, and a rotating shaft. A plurality of pressed vane
sections projecting from one surface are formed on the base plate
of each disk blade, and recessed spaces are formed in the pressed
vane sections, respectively. The projecting rear sections of the
pressed vane sections are affixed to the other surface of the base
plate of the adjacent disk blade, and disposed in the recessed
spaces of the pressed vane sections of the adjacent disk blade in
the mutually crossing direction. A part of a working gas is moved
in the recessed spaces, and moved forward in the rotating direction
over the projecting rear sections.
Inventors: |
Matsushita; Hiroaki;
(Chiba-shi, JP) |
Assignee: |
MAC CO., LTD.
Togane-shi, Chiba
JP
|
Family ID: |
41036696 |
Appl. No.: |
13/120839 |
Filed: |
June 15, 2009 |
PCT Filed: |
June 15, 2009 |
PCT NO: |
PCT/JP2009/061265 |
371 Date: |
March 24, 2011 |
Current U.S.
Class: |
416/204A |
Current CPC
Class: |
F05D 2250/182 20130101;
Y02T 50/673 20130101; F01D 5/048 20130101; F01D 15/005 20130101;
Y02T 50/60 20130101; F04D 29/023 20130101; F01D 1/22 20130101; F04D
29/281 20130101; F01D 1/34 20130101; F05D 2220/60 20130101; F05D
2230/237 20130101 |
Class at
Publication: |
416/204.A |
International
Class: |
F01D 5/02 20060101
F01D005/02 |
Foreign Application Data
Date |
Code |
Application Number |
Nov 28, 2008 |
JP |
2008-303877 |
Claims
1. An impeller for a turbine, which is rotated by an impulsive
force of a working gas which is ejected, the impeller for a turbine
comprises: an impeller body which is made by fixing two or more
types of press-formed disk blades in an alternately stacked state
using brazing method; a base plate to which the impeller body is
fixed; and a rotating shaft which is fixed to the base plate,
wherein the disk blade has a basal portion formed in annular
disk-shape, and a plurality of elongated pressed vane portions
which are disposed so as to connect an inner circumferential edge
and an outer circumferential edge of the basal portion and which
projects from one surface side of the basal portion, thereby being
capable of applying the impulsive force of the working gas, is
provided at the basal portion, and a recessed space, where an other
surface side of the basal portion is in an opened state, is formed
in each pressed vane portion, and where the pressed vane portion is
configured such that a projecting rear portion which is the most
protruded ridge portion thereof is disposed so as to be fixed to
the surface of the other side of the basal portion of the adjacent
disk blade using brazing method and to intersect the recessed space
of the pressed vane portion of the adjacent disk blade at an
intersecting communication space portion, and the pressed vane
portion is configured such that a portion of the working gas which
imparts the impulsive force to the pressed vane portion moves in
the recessed space of the adjacent disk blade through the
intersecting communication space portion and moves forward in the
rotational direction beyond the projecting rear portion of the
pressed vane portion in the intersecting communication space
portion.
2. The impeller for a turbine according to claim 1, wherein the
pressed vane portions of one type of disk blade are disposed in the
radial direction from the inner circumferential edge toward the
outer circumferential edge of the basal portion.
3. The impeller for a turbine according to claim 2, wherein the
pressed vane portions of the other type of disk blade are disposed
in a direction in which a position in the outer circumferential
edge is displaced backward in the rotational direction from a
standard direction, which is the radial direction from the inner
circumferential edge toward the outer circumferential edge of the
basal portion.
4. The impeller for a turbine according to claim 2, wherein the
pressed vane portions of the other type of disk blade are disposed
in a direction in which a position in the outer circumferential
edge is displaced forward in the rotational direction from a
standard direction, which is the radial direction from the inner
circumferential edge toward the outer circumferential edge of the
basal portion.
5. The impeller for a turbine according to claim 1 wherein the
inner circumferential edge of the basal portion of one type of disk
blade has a larger diameter than the inner circumferential edge of
the other type of disk blade, or the inner circumferential edge of
the basal portion of the other type of disk blade has a larger
diameter than the inner circumferential edge of one type of disk
blade.
6. The impeller for a turbine according to claim 1, wherein the
outer circumferential edge of the basal portion of one type of disk
blade has a smaller diameter than the outer circumferential edge of
the other type of disk blade, or the outer circumferential edge of
the basal portion of the other type of disk blade has a smaller
diameter than the outer circumferential edge of one type of disk
blade.
Description
TECHNICAL FIELD
[0001] The present invention mainly relates to an impeller for a
turbine, which is built to be freely rotatable in a casing and is
rotated by an impulsive force of an expanded suitable working gas
(for example, Freon gas or the like that is a heat medium) which is
ejected from an inlet of the casing at high speed, being received
by a plurality of vane portions, and drives a power generator or
the like by using the rotational force, and in particular, to an
impeller for a turbine, which is devised so as to be able to
generate a well-balanced and stable rotational force by efficiently
using an impulsive force of the working gas, to be able to be
easily manufactured in a simple configuration, to be able to be
configured to be small, light weight, and compact, to be suitable
for mass production, to significantly reduce costs, to be excellent
in versatility, and to be economical.
BACKGROUND ART
[0002] In the past, as this type of impeller for a turbine, various
impellers for turbines have been provided, and for example, in
Japanese Unexamined Patent Application Publication No. 2003-201802,
there is an impeller for a turbine shown as a prior example (FIG.
6). Such a prior example is an impeller for a turbine, in which a
complicated three-dimensional curvature processing is carried out
in each of a number of vanes (blades) and which is made so as to be
able to convert the impulsive force of a working gas into a
rotational force with high efficiency.
[0003] Also, in Japanese Unexamined Patent Application Publication
No. SHO58-140404, a turbine blade of a turbine for a refrigeration
cycle is disclosed. This is a turbine blade which is incorporated
in the inside of a turbine that is incorporated in a refrigeration
cycle in order to extract power by using high speed rotation after
expansion in the refrigeration cycle, wherein the blade is made
into an approximate disk shape and a plurality of protrusions is
formed (for example, by a press working) at the outer
circumferential portion of the disk.
[0004] However, in the related art of the impeller for a turbine
(as above-described, for example), in order to form each of a
number of blades (vanes) into a complicated three-dimensional
curved shape, which is required to apply many working processes,
and an impeller for a turbine manufactured in this way becomes
significantly high in cost, such that it becomes difficult to
provide the impeller at a low cost.
[0005] Also, in the related art of the turbine blade of a turbine
for a refrigeration cycle (as in the latter, for example), only a
relatively simple blade can be formed and there is a drawback in
that it is difficult to efficiently convert the impulsive force of
a working gas into a rotational force.
DISCLOSURE OF INVENTION
[0006] The object of the present invention is to resolve the
above-described drawbacks or the like and also provide an impeller
for a turbine, which can efficiently convert the impulsive force of
a working gas into a rotational force, which can obtain a
well-balanced and stable rotational force, which can be easily
manufactured in a simple configuration, which can be configured to
be small, light weight, and compact, which is suitable for mass
production, which significantly reduces costs, which is excellent
in versatility, and which is economical.
[0007] According to a first aspect of the present invention, there
is provided an impeller for a turbine, which includes an impeller
body which is made by fixing two or more types of press-formed disk
blades in an alternately stacked state using brazing method;
includes a base plate to which the impeller body is fixed; and
includes a rotating shaft which is fixed to the base plate and
which is rotated by an impulsive force of a working gas which is
ejected. The disk blade has a basal portion formed in annular
disk-shape, a plurality of elongated pressed vane portions which
are disposed so as to connect an inner circumferential edge and an
outer circumferential edge of the basal portion, which projects
from one surface side of the basal portion, thereby being capable
of applying the impulsive force of the working gas, is provided at
the basal portion, a recessed space where an other surface side of
the basal portion is in an opened state is formed in each pressed
vane portion, and the pressed vane portion is configured such that
a projecting rear portion which is the most protruded ridge portion
thereof is disposed so as to be fixed to the surface of the other
side of the basal portion of the adjacent disk blade using brazing
method and to intersect the recessed space of the pressed vane
portion of the adjacent disk blade at an intersecting communication
space portion and a portion of the working gas which imparts the
impulsive force to the pressed vane portion so as to move in the
recessed space of the adjacent disk blade through the intersecting
communication space portion and move forward in the rotational
direction beyond the projecting rear portion of the pressed vane
portion in the intersecting communication space portion.
[0008] Also, according to a second aspect of the present invention,
there is provided an impeller for a turbine, in which the pressed
vane portions of one type of disk blade are disposed in the radial
direction from the inner circumferential edge toward the outer
circumferential edge of the basal portion.
[0009] Also, according to a third aspect of the present invention,
there is provided an impeller for a turbine, in which the pressed
vane portions of the other type of disk blade are disposed in a
direction in which a position in the outer circumferential edge is
displaced backward in the rotational direction from a standard
direction, which is the radial direction from the inner
circumferential edge toward the outer circumferential edge of the
basal portion.
[0010] Also, according to a fourth aspect of the present invention,
there is provided an impeller for a turbine, in which the pressed
vane portions of the other type of disk blade are disposed in a
direction in which a position in the outer circumferential edge is
displaced forward in the rotational direction from a standard
direction, which is the radial direction from the inner
circumferential edge toward the outer circumferential edge of the
basal portion.
[0011] Also, according to a fifth aspect of the present invention,
there is provided an impeller for a turbine, in which the inner
circumferential edge of the basal portion of one type of disk blade
has a larger diameter than the inner circumferential edge of the
other type of disk blade or the inner circumferential edge of the
basal portion of the other type of disk blade has a larger diameter
than the inner circumferential edge of one type of disk blade.
[0012] Also, according to a sixth aspect of the present invention,
there is provided an impeller for a turbine, in which the outer
circumferential edge of the basal portion of one type of disk blade
has a smaller diameter than the outer circumferential edge of the
other type of disk blade or the outer circumferential edge of the
basal portion of the other type of disk blade has a smaller
diameter than the outer circumferential edge of one type of disk
blade.
[0013] Therefore, according to the first aspect of the present
invention, since the impeller for a turbine includes an impeller
body which is made by fixing two or more types of press-formed disk
blades in an alternately stacked state using brazing method, a base
plate to which the impeller body is fixed, and a rotating shaft
which is fixed to the base plate, it can be easily manufactured in
a simple configuration and be configured to be small, light weight,
and compact.
[0014] Further, the disk blade itself can be easily mass-produced,
so that a significant reduction in cost can be attained, whereby an
economical impeller for a turbine can be provided.
[0015] Furthermore, the disk blade itself is provided with a
plurality of pressed vane portions which connects the inner
circumferential edge and the outer circumferential edge of the disk
blade, so that it is possible to increase the strength and rigidity
thereof. In addition, since the projecting rear portion of the
pressed vane portion is disposed so as to intersect the recessed
space of the pressed vane portion of the adjacent disk blade and is
fixed using brazing method, it is possible to increase the strength
and rigidity of the entire impeller body. Consequently, it becomes
possible to use a thin plate material as the disk blade and it also
becomes possible to provide a lighter impeller for a turbine.
[0016] Then, since the pressed vane portion is disposed so as to
intersect the recessed space of the pressed vane portion of the
adjacent disk blade at the intersecting communication space portion
and the impeller body has two or more types of disk blade fixed to
each other in an alternately stacked state using brazing method,
the action of a force that the impeller body is subjected to the
impulsive force of the working gas becomes different in each of the
pressed vane portions of the two or more types of disk blades, so
that it is possible to rotate the impeller body in a well-balanced
and stable manner. Furthermore, the direction of each of the
pressed vane portions of the rotating impeller body always changes
with respect to the ejection direction of the working gas. However,
the impeller body relatively evenly receives the impulsive force of
the working gas at any rotational position, so that variations,
unevenness, or the like in the impulsive force which is imparted to
the impeller body can be suppressed, whereby it helps to rotate the
impeller body in a well-balanced and stable manner.
[0017] In particular, since the disk blade has a basal portion
formed in annular disk-shape, a plurality of elongated pressed vane
portions which is disposed so as to connect the inner
circumferential edge and the outer circumferential edge of the
basal portion and which projects from one surface side of the basal
portion, thereby being capable of applying the impulsive force of
the working gas, is provided at the basal portion, the recessed
space where the other surface side of the basal portion is in an
opened state is formed in each pressed vane portion, and the
pressed vane portion is configured such that the projecting rear
portion which is the most protruded ridge portion thereof is
disposed so as to be fixed to the surface of the other side of the
basal portion of the adjacent disk blade using brazing method and
to intersect the recessed space of the pressed vane portion of the
adjacent disk blade at the intersecting communication space portion
and a portion of the working gas which imparts the impulsive force
to the pressed vane portion so as to move in the recessed space of
the adjacent disk blade through the intersecting communication
space portion and move forward in the rotational direction beyond
the projecting rear portion of the pressed vane portion in the
intersecting communication space portion, it becomes possible to
constitute the impeller body by combining two or more types of disk
blades having different actions on the impulsive force of the
working gas and in the impeller body as a whole, a well-balanced
and more stable rotational force can be obtained by the impulsive
force of the working gas.
[0018] Further, an impeller for a turbine, in which a rotational
force depending a use or a purpose thereof can be obtained, can be
relatively easily constituted by changing the combination pattern
of the disk blades. Consequently, an impeller for a turbine having
excellent versatility can be provided easily and at a low cost.
[0019] In addition, a portion of the working gas which imparts an
impulsive force to the pressed vane portion moves in the recessed
space of the adjacent disk blade through the intersecting
communication space portion and moves forward in the rotational
direction beyond the projecting rear portion of the pressed vane
portion in the intersecting communication space portion, so that a
flow path of the working gas can be three-dimensionally configured
and it becomes possible to convert the impulsive force of the
working gas more efficiently into a rotational force.
[0020] Furthermore, a portion of the working gas which imparts an
impulsive force to the pressed vane portion moves to the negative
pressure surface side of the pressed vane portion forward in the
rotational direction beyond the projecting rear portion of the
pressed vane portion in the intersecting communication space
portion and this acts as elimination pressure of negative pressure
which is applied to the pressed vane portion, so that a rotational
force increases.
[0021] Also, according to the second aspect of the present
invention, since the pressed vane portions of one type of disk
blade are disposed in the radial direction from the inner
circumferential edge toward the outer circumferential edge of the
basal portion, a disk blade capable of being subjected to an
impulsive force which has a high rate where the rotary torque is
increased by a working gas is obtained.
[0022] Also, according to the third aspect of the present
invention, since the pressed vane portions of the other type of
disk blade are disposed in a direction in which a position in the
outer circumferential edge is displaced backward in the rotational
direction from a standard direction, which is the radial direction
from the inner circumferential edge toward the outer
circumferential edge of the basal portion, a disk blade capable of
being subjected to an impulsive force which has a high rate where
the rotating speed is increased by a working gas is obtained.
[0023] Also, according to the fourth aspect of the present
invention, since the pressed vane portions of the other type of
disk blade are disposed in a direction in which a position in the
outer circumferential edge is displaced forward in the rotational
direction from a standard direction, which is the radial direction
from the inner circumferential edge toward the outer
circumferential edge of the basal portion, a disk blade capable of
being subjected to an impulsive force which has a high rate where
the rotating speed is increased by a working gas is obtained.
[0024] Also, according to the fifth aspect of the present
invention, since the inner circumferential edge of the basal
portion of one type of disk blade has a larger diameter than the
inner circumferential edge of the other type of disk blade or the
inner circumferential edge of the basal portion of the other type
of disk blade has a larger diameter than the inner circumferential
edge of one type of disk blade, the inner circumferential edge
portion of the basal portion of one type of disk blade is not
present in a space portion between the inner circumferential edges
of the basal portions of the other type of adjacent disk blades or
the inner circumferential edge portion of the basal portion of the
other type of disk blade is not present in a space portion between
the inner circumferential edges of the basal portions of one type
of adjacent disk blades, such that passage resistance of the
working gas in the space portion is reduced, whereby loss of
rotational energy which is imparted to the impeller for a turbine
by the working gas can be reduced.
[0025] Further, according to the sixth aspect of the present
invention, since the outer circumferential edge of the basal
portion of one type of disk blade has a smaller diameter than the
outer circumferential edge of the other type of disk blade or the
outer circumferential edge of the basal portion of the other type
of disk blade has a smaller diameter than the outer circumferential
edge of one type of disk blade, the outer circumferential edge
portion of the basal portion of one type of disk blade is not
present in a space portion between the outer circumferential edges
of the basal portions of the other type of adjacent disk blades or
the outer circumferential edge portion of the basal portion of the
other type of disk blade is not present in a space portion between
the outer circumferential edges of the basal portions of one type
of adjacent disk blades, such that passage resistance of the
working gas in the space portion is reduced, whereby loss of
rotational energy which is imparted to the impeller for a turbine
by the working gas can be reduced.
BRIEF DESCRIPTION OF DRAWINGS
[0026] FIG. 1 is a schematic side view with a partial cutaway,
illustrating a state where an impeller for a turbine according to
the present invention is incorporated in a casing.
[0027] FIG. 2 is a fragmentary exploded perspective view with a
portion omitted, illustrating the impeller for a turbine according
to the present invention.
[0028] FIG. 3 is a front view illustrating a disk blade of the
impeller for a turbine according to the present invention.
[0029] FIG. 4 is a front view illustrating another disk blade of
the impeller for a turbine according to the present invention.
[0030] FIG. 5 is a schematic front view illustrating an impeller
body of the impeller for a turbine according to the present
invention.
[0031] FIG. 6 is a cross-sectional side view with a portion
omitted, illustrating the impeller for a turbine according to the
present invention.
[0032] FIG. 7 is a fragmentary schematic front view illustrating an
intersecting communication space portion of the impeller for a
turbine according to the present invention.
[0033] FIGS. 8(I) and 8(II) show fragmentary end views of the
impeller for a turbine according to the present invention, wherein
FIG. 8(I) is a fragmentary end view in the intersecting
communication space portion and FIG. 8(II) is a fragmentary end
view in portions other than the intersecting communication space
portion.
[0034] FIG. 9 is a front view illustrating another disk blade of
the impeller for a turbine according to the present invention.
[0035] FIG. 10 is a front view illustrating another disk blade of
the impeller for a turbine according to the present invention.
[0036] FIG. 11 is a front view illustrating another disk blade of
the impeller for a turbine according to the present invention.
[0037] FIG. 12 is a front view illustrating another disk blade of
the impeller for a turbine according to the present invention.
[0038] FIG. 13 is a schematic front view illustrating an impeller
body of another impeller for a turbine according to the present
invention.
[0039] FIG. 14 is a schematic front view illustrating an impeller
body of another impeller for a turbine according to the present
invention.
[0040] FIG. 15 is a schematic cross-sectional side view
illustrating a portion of another impeller for a turbine according
to the present invention.
[0041] FIG. 16 is a schematic cross-sectional side view
illustrating a portion of another impeller for a turbine according
to the present invention.
EMBODIMENTS OF THE INVENTION
[0042] The present invention which is described below on the basis
of an illustrated example is as follows.
[0043] The present invention is an impeller for a turbine, which is
rotatably built in a casing D having an inlet 30 and an outlet 31
and also is made so as to rotate by an impulsive force of an
expanded working gas (for example, Freon gas or the like that is a
heat medium), which is ejected from the inlet 30 of the casing D at
high speed, being received by a plurality of pressed vane portions
11 and drive a power generator or the like by using the rotational
force.
[0044] Then, the impeller for a turbine includes an impeller body
which is made by fixing two or more types of press-formed disk
blades A in an alternately stacked state using brazing method, a
base plate B to which the impeller body is fixed, and a rotating
shaft C which is fixed to the base plate B.
[0045] Further, the disk blade A has a basal portion 10 formed in
annular disk-shape, at the basal portion 10, a plurality of
elongated pressed vane portions 11 is disposed so as to
appropriately connect an inner circumferential edge and an outer
circumferential edge of the basal portion and which projects from
one surface side of the basal portion, thereby being capable of
applying the impulsive force of the working gas, and a recessed
space 12 where the other surface side of the basal portion 10 is in
an opened state is formed in each pressed vane portion 11.
[0046] Moreover, the pressed vane portion 11 is configured such
that a projecting rear portion 11a which is the most protruded
ridge portion thereof is disposed so as to be fixed to the surface
of the other side of the basal portion 10 of the adjacent disk
blade A and to intersect the recessed space 12 of the pressed vane
portion 11 of the adjacent disk blade A at an intersecting
communication space portion 13 and a portion of the working gas
which imparts the impulsive force to the pressed vane portion 11 so
as to move in the recessed space 12 of the adjacent disk blade A
through the intersecting communication space portion 13 and to move
forward in the rotational direction beyond the projecting rear
portion 11a of the pressed vane portion 11 in the intersecting
communication space portion 13.
[0047] Also, the pressed vane portions 11 of one type of disk blade
A are disposed in the radial direction from the inner
circumferential edge toward the outer circumferential edge of the
basal portion 10.
[0048] Further, the pressed vane portions 11 of the other type of
disk blade A are disposed in a direction in which a position in the
outer circumferential edge is displaced backward in the rotational
direction from a standard direction, which is the radial direction
from the inner circumferential edge toward the outer
circumferential edge of the basal portion 10.
[0049] Then, the pressed vane portions 11 of the other type of disk
blade A are disposed in a direction in which a position in the
outer circumferential edge is displaced forward in the rotational
direction from a standard direction, which is the radial direction
from the inner circumferential edge toward the outer
circumferential edge of the basal portion 10.
Example
[0050] The disk blade A which is used in the impeller for a turbine
is constituted by, for example, a metallic (for example, stainless
steel) disk having a relatively thin annular disk shape and
excellent corrosion resistance. Further, the disk blade is
configured such that a number of pressed vane portions 11 are
provided at the disk by a single (or, a plurality is also
acceptable) press working and also a number of pressed vane
portions 11 project from one surface side of the disk. Furthermore,
the pressed vane portions 11 are formed from the inner
circumferential edge to the outer circumferential edge of the disk.
Also, a portion of the disk, in which the pressed vane portions 11
are not formed by the press working, becomes the basal portion 10,
the inside of the projected pressed vane portion 11 becomes the
recessed space 12, and the most protruded ridge portion of the
pressed vane portion 11 becomes the projecting rear portion
11a.
[0051] Further, two or more types of disk blades A, in which the
dimensions, the shapes, the number, or the disposition state of the
pressed vane portions 11 or the dimension or the like of the basal
portion 10 is changed, are formed, and the impeller bodies, in
which the combination patterns of the disk blades A are different
from each other, can be freely constituted by appropriately
selecting these disk blades A and also fixing the appropriate
number of disk blades in an alternately stacked state.
[0052] Then, describing each disk blade A of the illustrated
examples, first, the disk blade A(A1) of FIG. 3 (and FIG. 2) is
configured such that a plurality (for example, 24 pieces) of
pressed vane portions 11 is disposed in the radial direction from
the inner circumferential edge toward the outer circumferential
edge of the basal portion 10.
[0053] Also, the disk blade A(A2) of FIG. 4 (and FIG. 2) is
configured such that a plurality (for example, 24 pieces) of
pressed vane portions 11 is disposed in a direction in which a
position in the outer circumferential edge is varied from a
standard direction, which is the radial direction from the inner
circumferential edge toward the outer circumferential edge of the
basal portion 10, forward in the rotational direction (or, may be
disposed in a direction in which a position in the outer
circumferential edge is varied backward in the rotational
direction).
[0054] Also, the disk blade A(A4) of FIG. 9 is configured such that
a plurality (for example, 12 pieces) of pressed vane portions 11 is
disposed in the radial direction from the inner circumferential
edge toward the outer circumferential edge of the basal portion
10.
[0055] Then, the disk blade A(A5) of FIG. 10 is configured such
that a plurality (for example, 12 pieces) of pressed vane portions
11 is disposed in a direction in which a position in the outer
circumferential edge is varied from a standard direction, which is
the radial direction from the inner circumferential edge toward the
outer circumferential edge of the basal portion 10, forward (or,
backward is also acceptable) in the rotational direction.
[0056] Then, the disk blade A(A6) of FIG. 11 is configured such
that the inner circumferential edge of the basal portion 10 has a
larger diameter than the inner circumferential edge of another disk
blade A and a plurality (for example, 12 pieces) of pressed vane
portions 11 is disposed in the radial direction from the inner
circumferential edge toward the outer circumferential edge of the
basal portion 10.
[0057] In addition, the disk blade A(A7) of FIG. 12 is configured
such that the outer circumferential edge of the basal portion 10
has a smaller diameter than the outer circumferential edge of
another disk blade A and a plurality (for example, 12 pieces) of
pressed vane portions 11 is disposed in the radial direction from
the inner circumferential edge toward the outer circumferential
edge of the basal portion 10.
[0058] Also, the impeller body which is constituted by using the
disk blades A as described above is constituted by fixing two or
more types of disk blades A in an alternately stacked state using
brazing method.
[0059] Specifically, the impeller body shown in FIG. 5 is
constituted by fixing the disk blade A(A1) of FIG. 3 and the disk
blade A(A2) of FIG. 4 in an alternately stacked state using brazing
method. Further, the impeller body is constituted such that when
the projecting rear portion 11a which is the most protruded ridge
portion of the pressed vane portion 11 is fixed to the surface of
the other side of the basal portion 10 of the adjacent disk blade
A, the projecting rear portion 11a is disposed so as to intersect
the recessed space 12 of the pressed vane portion 11 of the
adjacent disk blade A at the intersecting communication space
portion 13 and furthermore, the intersecting communication space
portion 13 is provided at two locations with respect to one pressed
vane portion 11. That is, the strength and rigidity of the entire
impeller body increase and excellent durability is obtained.
Further, it becomes possible to more complicatedly conduct the
working gas by the intersecting communication space portions 13,
and an impeller body is formed in which a superior (for example,
well-balanced, efficient, and low in energy loss) rotational force
is provided.
[0060] In addition, a configuration is made such that in the
intersecting communication space portion 13, a portion of the
working gas which imparts an impulsive force to the pressed vane
portion 11 so as to move in the recessed space 12 of the adjacent
disk blade A and to move forward in the rotational direction beyond
the projecting rear portion 11a of the pressed vane portion 11.
[0061] The base plate B is formed, for example, into a metallic
thick disk shape, in which a mounting hole 15 for the rotating
shaft C is perforated at the center thereof, and is fixed to a base
end surface portion of the impeller body using brazing method.
[0062] The symbol B1 in the drawings indicates a leading end plate
which is fixed to a leading end surface portion of the impeller
body using brazing method, and the leading end plate B1 is formed
into an annular disk shape using a suitable metal material and
provided so as to increase the strength or the rigidity of the
leading end surface portion of the impeller body.
[0063] The rotating shaft C is rotatably mounted in the casing D, a
case of a power generator section, which is provided continuously
to the casing D, or the like (refer to FIG. 1) and constituted so
as to be able to smoothly rotate without loss and also stably
support the impeller body. Also, a configuration is made such that
a male screw portion is formed at a leading end portion of the
rotating shaft C and the impeller body can be reliably and easily
fixed to the rotating shaft C by a mounting nut 20 capable of being
thread-engaged with the male screw portion.
[0064] As for the brazing method for fixing the disk blades A to
each other or fixing the base plate B or the leading end plate B1,
for example, a method is adopted which can dissolve only a metal
binder material (for example, copper, nickel, or the like) having a
melting point lower than that of the disk blade A (made of
stainless steel), the base plate B, or the leading end plate B1 and
then reliably fix the disk blades A to each other or fix the base
plate B or the leading end plate B1 by using it as a melt adhesive
agent.
[0065] Also, when fixing a plurality of disk blades A in a stacked
state, for example, a binder material such as a copper foil having
a melting point lower than that of the disk blade A is stacked
between the disk blades A which are stacked and the binder material
is then melted by heating them in a vacuum, so that contact
portions between a plurality of disk blades A (the projecting rear
portion 11a of the pressed vane portion 11 and the other surface of
the basal portion 10 in the adjacent disk blades A) can be simply
and reliably vacuum-brazed by the melted binder material.
Incidentally, this method is also used when fixing the base plate B
or the leading end plate B1 to the impeller body.
[0066] Also, the impeller body shown in FIGS. 13 and 15 is an
impeller body constituted by fixing the disk blade A(A6) of FIG. 11
and the disk blade A(A5) of FIG. 10 in an alternately stacked state
using brazing method, and this is constituted such that the inner
circumferential edge of the basal portion 10 of the disk blade
A(A6) has a larger diameter than the inner circumferential edge of
the disk blade A(A5), so that the inner circumferential edge
portion of the basal portion 10 of the disk blade A(A6) is not
present in a space portion between the inner circumferential edges
of the basal portions 10 of the adjacent disk blades A(A5), whereby
passage resistance of the working gas in the space portion is
reduced, and thus formed such that loss of rotational energy which
is imparted to the impeller for a turbine by the working gas can be
reduced.
[0067] Further, the impeller body shown in FIGS. 14 and 16 is an
impeller body constituted by fixing the disk blade A(A7) of FIG. 12
and the disk blade A(A5) of FIG. 10 in an alternately stacked state
using brazing method, and this is constituted such that the outer
circumferential edge of the basal portion 10 of the disk blade
A(A7) has a smaller diameter than the outer circumferential edge of
the disk blade A(A5), so that the outer circumferential edge
portion of the basal portion 10 of the disk blade A(A7) is not
present in a space portion between the outer circumferential edges
of the basal portions 10 of the adjacent disk blades A(A5), whereby
passage resistance of the working gas in the space portion is
reduced, and thus the impeller body formed such that loss of
rotational energy which is imparted to the impeller for a turbine
by the working gas can be reduced.
[0068] As for the casing D, for example, a casing provided with the
inlet 30, through which the working gas is blown in, and the outlet
31, through which the working gas is discharged, is adopted.
Furthermore, the inlet 30 is opened at an outer circumferential
wall portion of the casing D and the outlet 31 is opened at the
center of a side wall portion of one side of the casing D. Also, in
the inlet 30 of the casing D, an angle or the like, at which the
working gas is blown in, can be set and changed freely and
appropriately.
[0069] The impeller for a turbine according to the present
invention is constituted as described above and is used, for
example, to generate a rotational force in the impeller for a
turbine by ejecting expanded working gas from the inlet 30 of the
casing D at high speed, thereby making the impulsive force of the
working gas act on a plurality of pressed vane portions 11, and
drive a power generator or the like by using the rotational
force.
[0070] However, the impeller for a turbine according to the present
invention is not limited only to a usage example as described above
and can also be used. For example, as an impeller of a centrifugal
blower or an impeller of a pump which is formed so as to connect a
prime mover such as a motor to the rotating shaft C of the impeller
for a turbine and be able to compulsorily rotate the impeller for a
turbine by using a rotational force of the prime mover.
[0071] In addition, although the embodiments of the present
invention have been described in detail, the combination and
arrangement of the parts for the embodiments can be changed in
various ways without violating the spirit and scope of the
invention as defined in the appended claims.
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