U.S. patent application number 13/357876 was filed with the patent office on 2012-10-04 for rotor of rotary machine and rotary machine.
Invention is credited to Kenji Kawasaki, Takashi Nakano, Shin NISHIMOTO, Yoshinori Tanaka, Ryuichi Yamamoto.
Application Number | 20120251307 13/357876 |
Document ID | / |
Family ID | 46927499 |
Filed Date | 2012-10-04 |
United States Patent
Application |
20120251307 |
Kind Code |
A1 |
NISHIMOTO; Shin ; et
al. |
October 4, 2012 |
ROTOR OF ROTARY MACHINE AND ROTARY MACHINE
Abstract
A rotor (10) of a rotary machine (T1) according to the invention
includes a plurality of rotor members (20, 30, and 40) which are
joined to each other in the axial direction in which the axis (P)
extends, and among the plurality of rotor members (20, 30 and 40),
the first rotor member (30) in hydraulic fluid injection portions
(3a and 3b) of a passageway (3) is formed of Ni-based alloy so that
the inside thereof is hollow throughout the entire length in the
axial direction.
Inventors: |
NISHIMOTO; Shin; (Tokyo,
JP) ; Tanaka; Yoshinori; (Tokyo, JP) ; Nakano;
Takashi; (Tokyo, JP) ; Kawasaki; Kenji;
(Tokyo, JP) ; Yamamoto; Ryuichi; (Tokyo,
JP) |
Family ID: |
46927499 |
Appl. No.: |
13/357876 |
Filed: |
January 25, 2012 |
Current U.S.
Class: |
415/198.1 ;
416/232 |
Current CPC
Class: |
F05D 2300/177 20130101;
F05D 2220/31 20130101; F01D 25/10 20130101; F05D 2300/171 20130101;
F01D 5/063 20130101; C22C 19/056 20130101; C22C 19/057 20130101;
C22C 19/055 20130101; F01D 1/04 20130101; F05D 2260/941 20130101;
F01D 5/06 20130101; F01D 25/24 20130101 |
Class at
Publication: |
415/198.1 ;
416/232 |
International
Class: |
F01D 5/18 20060101
F01D005/18 |
Foreign Application Data
Date |
Code |
Application Number |
Mar 30, 2011 |
JP |
2011-074206 |
Claims
1. A rotor of a rotary machine of which an outer peripheral portion
extending about an axis is surrounded by a stator and in which a
hydraulic fluid circulates in a passageway defined between the
stator and the outer peripheral portion, the rotor comprising: a
plurality of rotor members that are joined to each other in the
axial direction in which the axis extends, wherein a first rotor
member which is included in the plurality of rotor members and
which is located in a hydraulic fluid injection portion of the
passageway is formed of an Ni-based alloy, and the inside of the
first rotor member is hollow throughout the entire length in the
axial direction.
2. The rotor of the rotary machine according to claim 1, wherein
the plurality of rotor members include a second rotor member that
is adjacent to the first rotor member in the axial direction and is
formed of high Cr-steel.
3. The rotor of the rotary machine according to claim 1, wherein
the first rotor member is formed so that the thickness of the
center portion in the axial direction is greater than or equal to
the thickness of the end portion in the axial direction and a value
of a ratio between the inner diameter and the outer diameter at the
center portion in the axial direction is greater than or equal to
1/2.
4. The rotor of the rotary machine according to claim 1, wherein a
plurality of the hydraulic fluid injection portions is formed, and
wherein the inner diameters of at least two or more of the
plurality of hydraulic fluid injection portions are different from
each other in the first rotor member.
5. The rotor of the rotary machine according to claim 1, wherein
the inner diameters of a plurality of portions in the axial
direction are different from each other in the first rotor
member.
6. The rotor of the rotary machine according to claim 1, wherein in
at least part of the first rotor member in the axial direction, a
hole is formed in a tapered shaped so that the inner diameter
gradually decreases toward one end side of the rotor member from
the other end side.
7. The rotor of the rotary machine according to claim 1, wherein
the Ni-based alloy includes 0.15 wt % or less of C, 1 wt % or less
of Si, 1 wt % or less of Mn, 5 to 15 wt % of Cr, 17 to 25 wt % of
including one or two or more of Mo, W, and Re; Mo+(W+Re)/2, 0.2 to
2 wt % of Al, 0.5 to 4.5 wt % of Ti, 10 wt % or less of Fe,
including one or two of 0.02 wt % or less of B and 0.2 wt % or less
of Zr, 2.5 to 7.0 at % of Al+Ti, and the remainder of Ni and
inevitable impurities.
8. The rotor of the rotary machine according to claim 1, wherein
the Ni-based alloy includes 0.15 wt % or less of C, 1 wt % or less
of Si, 1 wt % or less of Mn, 5 to 20 wt % of Cr, 17 to 26 wt % of
Mo, 17 to 27 wt % of Mo+(W+Re)/2, 0.1 to 2 wt % of Al, 0.1 to 2 wt
% of Ti, 10 wt % or less of Fe, 0.02 wt % or less of B, 0.2 wt % or
less of Zr, 1 to 5.5 at % of Al+Ti, and the remainder of Ni and
inevitable impurities.
9. The rotor of the rotary machine according to claim 1, wherein
the Ni-based alloy includes 0.15 wt % or less of C, 1 wt % or less
of Si, 1 wt % or less of Mn, 5 to 20 wt % of Cr, 17 to 27 wt % of
including one or two or more of Mo, W, and Re; Mo+(W+Re)/2, 0.1 to
2 wt % of Al, 0.1 to 2 wt % of Ti, 10 wt % or less of Fe, 0.001 to
0.02 wt % of B, 0.001 to 0.2 wt % of Zr, 1.5 wt % or less of
Nb+Ta/2, 5 wt % or less of Co, and the remainder of Ni and
inevitable impurities.
10. The rotor of the rotary machine according to claim 1, wherein
the Ni-based alloy includes 0.15 wt % or less of C, 1 wt % or less
of Si, 1 wt % or less of Mn, 5 to 20 wt % of Cr, 10 wt % or less of
W, 5 to 20 wt % of including one or two or more of Mo, W, and Re;
Mo+(W+Re)/2, 0.1 to 2.5 wt % of Al, 0.10 to 0.95 wt % of Ti, 4 wt %
or less of Fe, 0.001 to 0.02 wt % of B, 0.001 to 0.2 wt % of Zr,
1.5 wt % or less of Nb+Ta/2, 2.0 to 6.5 at % of Al+Ti+Nb+Ta, and
the remainder of Ni and inevitable impurities.
11. The rotor of the rotary machine according to claim 1, wherein
the Ni-based alloy includes 0.005 to 0.1 wt % of C, 8 to 15 wt % of
Cr, 5 to 20 wt % of W, 1 to 7 wt % of Mo, 0.5 to 1.0 wt % of Al,
1.0 to 2.5 wt % of Ti, and the remainder of Ni and inevitable
impurities.
12. The rotor of the rotary machine according to claim 1, wherein
the Ni-based alloy includes 0.005 to 0.15 wt % of C, 8 to 22 wt %
of Cr, 5 to 30 wt % of Co, 5 to 20 wt % of W, 1 to 9 wt % of Mo,
0.1 to 2.0 wt % of Al, 0.3 to 2.5 wt % of Ti, 0.015 wt % or less of
B, 0.01 wt % or less of Mg, and the remainder of Ni and inevitable
impurities.
13. A rotary machine comprising: the rotor of the rotary machine
according to claim 1, and a stator which surrounds the rotor and in
which a hydraulic fluid is injected into a passageway defined
between the stator and the rotor.
14. A rotary machine comprising: the rotor of the rotary machine
according to claim 2, and a stator which surrounds the rotor and in
which a hydraulic fluid is injected into a passageway defined
between the stator and the rotor.
15. A rotary machine comprising: the rotor of the rotary machine
according to claim 3, and a stator which surrounds the rotor and in
which a hydraulic fluid is injected into a passageway defined
between the stator and the rotor.
16. A rotary machine comprising: the rotor of the rotary machine
according to claim 4, and a stator which surrounds the rotor and in
which a hydraulic fluid is injected into a passageway defined
between the stator and the rotor.
17. A rotary machine comprising: the rotor of the rotary machine
according to claim 5, and a stator which surrounds the rotor and in
which a hydraulic fluid is injected into a passageway defined
between the stator and the rotor.
18. A rotary machine comprising: the rotor of the rotary machine
according to claim 6, and a stator which surrounds the rotor and in
which a hydraulic fluid is injected into a passageway defined
between the stator and the rotor.
19. A rotary machine comprising: the rotor of the rotary machine
according to claim 7, and a stator which surrounds the rotor and in
which a hydraulic fluid is injected into a passageway defined
between the stator and the rotor.
20. A rotary machine comprising: the rotor of the rotary machine
according to claim 8, and a stator which surrounds the rotor and in
which a hydraulic fluid is injected into a passageway defined
between the stator and the rotor.
Description
TECHNICAL FIELD
[0001] The present invention relates to a rotor of a rotary machine
and a rotary machine.
[0002] Priority is claimed on Japanese Patent Application No.
2011-74206, filed Mar. 30, 2011, the content of which is
incorporated herein by reference.
BACKGROUND ART
[0003] Recently, in steam-power generation using a steam turbine,
electricity is usually generated at 600.degree. C. or less. In many
cases, main components such as a turbine rotor and a rotor vane
constituting the steam turbine and used under these conditions are
formed of, for example, high Cr-steel (high-chrome steel and
ferritic heat resistant steel) such as 12Cr steel.
[0004] Incidentally, in recent years, there has been a demand for
generating electricity at conditions in which the steam is
700.degree. C. or more in order to meet requirements for a
reduction in the discharge of CO.sub.2 and further improvements in
thermal efficiency. However, due to the insufficient
high-temperature strength of the main components, it is not
desirable to use ferritic heat resistant steel under these
conditions.
[0005] Therefore, in order to ensure a higher high-temperature
strength, a Ni-based alloy (nickel base alloy) is used for the main
components. However, when the Ni-based alloy is used, there are
disadvantages in that the main components may not be easily made in
large sizes and the cost may increase.
[0006] In Patent Document 1 below, in order to both allow an
increase in size and suppress cost of the turbine rotor, a turbine
rotor is formed by joining a first member formed of a Ni-based
alloy to a second member formed of high Cr-steel by welding. Then,
the strength of the joint portion is ensured by using a Ni-based
alloy with a specific composition.
PRIOR ART DOCUMENT
Patent Document
[0007] Patent Document 1: PCT International Publication WO
2009/154243
SUMMARY OF THE INVENTION
Problem to be Solved by the Invention
[0008] Incidentally, the Ni-based alloy generally has a low thermal
conductivity and a large linear expansion coefficient. For this
reason, during the start-up of the steam turbine, the outside of
the turbine rotor (the Ni-based alloy) increases in temperature and
thermally expands so as to be larger than the inside thereof,
thereby causing a problem in that excessive stress is generated
inside the turbine rotor.
[0009] On the other hand, when the turbine rotor is warmed up
slowly so that the temperature thereof gradually increases as a
whole, the generation of thermal stress may be suppressed. However,
there is a problem in that rapid start-up of the steam turbine is
inhibited.
[0010] The invention is made in view of such circumstances, and it
is an object of the invention to allow rapid start-up of the rotary
machine and to suppress the thermal stress generated in the
rotor.
Means for Solving the Problems
[0011] In order to accomplish the above-described object, the
invention adopts the following means.
[0012] That is, according to the invention, there is provided a
rotor of a rotary machine of which an outer peripheral portion
extending along an axis is surrounded by a stator and in which a
hydraulic fluid circulates in a passageway defined between the
stator and the outer peripheral portion, the rotor including: a
plurality of rotor members that are joined to each other in the
axial direction in which the axis extends, wherein a first rotor
member which is included in the plurality of rotor members and
which is located in a hydraulic fluid injection portion of the
passageway is formed of an Ni-based alloy, and the inside of the
first rotor member is hollow throughout the entire length in the
axial direction.
[0013] In this way, since the inside of the first rotor member
which is formed of the Ni-based alloy is hollow throughout its
entire length in the axial direction, the thermal capacity of the
first rotor member becomes smaller than that of the case where the
inside is solid. Accordingly, when the rotary machine is rapidly
started up, a difference in the temperature which is generated
between the outside and the inside of the inner portion of the
first rotor member is suppressed, so that the temperature of the
first rotor member increases as a whole. Accordingly, it is
possible to suppress the thermal stress which is generated inside
the first rotor member. Thus, the rotary machine may be rapidly
started up and the thermal stress generated in the rotor may be
suppressed.
[0014] Further, the plurality of rotor members may include a second
rotor member that is adjacent to the first rotor member in the
axial direction and is formed of high Cr-steel.
[0015] In this way, since the plurality of rotor members include
the second rotor member which is adjacent to the first rotor member
in the axial direction and is formed of high Cr-steel, it is
possible to suppress an increase in the cost of the rotor compared
to the case where the entire rotor is formed of the Ni-based alloy.
Furthermore, since part of the rotor is formed of high Cr-steel
which is more easily molded than Ni-based alloy, the rotor may be
easily manufactured.
[0016] Further, the first rotor member may be formed so that the
thickness of the center portion in the axial direction is greater
than or equal to the thickness of the end portion in the axial
direction and the value of the ratio between the inner diameter and
the outer diameter at the center portion in the axial direction is
greater than or equal to 1/2.
[0017] In this way, it is possible to further suppress a difference
in the temperature which is generated between the outside and the
inside of the inner portion of the first rotor member, and further
suppress the thermal stress generated inside the first rotor
member. Further, it is possible to ensure the strength necessary
for the first rotor member.
[0018] Further, a plurality of the hydraulic fluid injection
portions may be formed, and the inner diameters of at least two or
more of the plurality of hydraulic fluid injection portions may be
different from each other in the first rotor member.
[0019] In this way, it is possible to adjust the temperature
distribution for each hydraulic fluid injection portion.
[0020] Further, the inner diameters of a plurality of portions in
the axial direction may be different from each other in the first
rotor member.
[0021] In this way, it is possible to adjust the temperature
distribution in a plurality of portions in the axial direction.
[0022] Further, in at least part of the first rotor member in the
axial direction, a hole may be formed in a tapered shaped so that
the inner diameter gradually decreases toward one end side of the
rotor member from the other end side.
[0023] In this way, it is possible to adjust the temperature of the
first rotor member in the axial direction.
[0024] Further, the Ni-based alloy may include 0.15 wt % or less of
C, 1 wt % or less of Si, 1 wt % or less of Mn, 5 to 15 wt % of Cr,
17 to 25 wt % of including one or two or more of Mo, W, and Re;
Mo+(W+Re)/2, 0.2 to 2 wt % of Al, 0.5 to 4.5 wt % of Ti, 10 wt % or
less of Fe, including one or two of 0.02 wt % or less of B and 0.2
wt % or less of Zr, 2.5 to 7.0 at % of Al+Ti, and the remainder of
Ni and inevitable impurities.
[0025] Further, the Ni-based alloy may include 0.15 wt % or less of
C, 1 wt % or less of Si, 1 wt % or less of Mn, 5 to 20 wt % of Cr,
17 to 26 wt % of Mo, 17 to 27 wt % of Mo+(W+Re)/2, 0.1 to 2 wt % of
Al, 0.1 to 2 wt % of Ti, 10 wt % or less of Fe, 0.02 wt % or less
of B, 0.2 wt % or less of Zr, 1 to 5.5 at % of Al+Ti, and the
remainder of Ni and inevitable impurities.
[0026] Further, the Ni-based alloy may include 0.15 wt % or less of
C, 1 wt % or less of Si, 1 wt % or less of Mn, 5 to 20 wt % of Cr,
17 to 27 wt % of including one or two or more of Mo, W, and Re;
Mo+(W+Re)/2, 0.1 to 2 wt % of Al, 0.1 to 2 wt % of Ti, 10 wt % or
less of Fe, 0.001 to 0.02 wt % of B, 0.001 to 0.2 wt % of Zr, 1.5
wt % or less of Nb+Ta/2, 5 wt % or less of Co, and the remainder of
Ni and inevitable impurities.
[0027] Further, the Ni-based alloy may include 0.15 wt % or less of
C, 1 wt % or less of Si, 1 wt % or less of Mn, 5 to 20 wt % of Cr,
10 wt % or less of W, 5 to 20 wt % of including one or two or more
of Mo, W, and Re; Mo+(W+Re)/2, 0.1 to 2.5 wt % of Al, 0.10 to 0.95
wt % of Ti, 4 wt % or less of Fe, 0.001 to 0.02 wt % of B, 0.001 to
0.2 wt % of Zr, 1.5 wt % or less of Nb+Ta/2, 2.0 to 6.5 at % of
Al+Ti+Nb+Ta, and the remainder of Ni and inevitable impurities.
[0028] Further, the Ni-based alloy may include 0.005 to 0.1 wt % of
C, 8 to 15 wt % of Cr, 5 to 20 wt % of W, 1 to 7 wt % of Mo, 0.5 to
1.0 wt % of Al, 1.0 to 2.5 wt % of Ti, and the remainder of Ni and
inevitable impurities.
[0029] Further, the Ni-based alloy may include 0.005 to 0.15 wt %
of C, 8 to 22 wt % of Cr, 5 to 30 wt % of Co, 5 to 20 wt % of W, 1
to 9 wt % of Mo, 0.1 to 2.0 wt % of Al, 0.3 to 2.5 wt % of Ti,
0.015 wt % or less of B, 0.01 wt % or less of Mg, and the remainder
of Ni and inevitable impurities.
[0030] That is, when the first rotor member is formed of the
Ni-based alloy with the abovementioned compositions, it is possible
to ensure the strength of the joint portion with the second rotor
member formed of the high Cr-steel.
[0031] Furthermore, according to the invention, there is provided a
rotary machine including: a rotor of one of the above-described
rotary machines and a stator which surrounds the rotor and in which
a hydraulic fluid is injected into a passageway defined between the
stator and the rotor.
[0032] In this way, even when the Ni-based alloy is used under
conditions in which the hydraulic fluid is comparatively hot, the
rotary machine may be rapidly started up and the thermal stress
generated in the rotor may be suppressed. Accordingly, satisfactory
running performance may be obtained and damage to the rotor may be
prevented. Then, since the hydraulic fluid is set to a
comparatively high temperature, requirements for a reduction in the
discharge of CO.sub.2 or further improvements in thermal efficiency
may be sufficiently handled.
Advantageous Effect of the Invention
[0033] According to the rotor of the rotary machine of the
invention, it is possible to rapidly start up the rotary machine
and suppress the thermal stress generated in the rotor.
[0034] Further, according to the rotary machine of the invention,
it is possible to obtain a satisfactory running performance and
prevent damage to the rotor.
BRIEF DESCRIPTION OF THE DRAWINGS
[0035] FIG. 1 is a cross-sectional view illustrating a schematic
configuration of a high and intermediate pressure turbine T1
according to a first embodiment of the invention, and a meridian
cross-sectional view including the axis P of the high and
intermediate pressure turbine T1.
[0036] FIG. 2 is an enlarged cross-sectional view illustrating a
shaft body 11 according to an embodiment of the invention.
[0037] FIG. 3 is an enlarged cross-sectional view illustrating a
shaft body 11A in a high and intermediate pressure turbine T2
according to a second embodiment of the invention.
[0038] FIG. 4 is an enlarged cross-sectional view illustrating a
shaft body 11B in a high and intermediate pressure turbine T3
according to a third embodiment of the invention.
[0039] FIG. 5 is an enlarged cross-sectional view illustrating a
shaft body 11C in a high and intermediate pressure turbine T4
according to a fourth embodiment of the invention.
MODE FOR CARRYING OUT THE INVENTION
[0040] Hereinafter, embodiments of the invention will be described
by referring to the drawings.
First Embodiment
[0041] FIG. 1 is a cross-sectional view illustrating a schematic
configuration of a high and intermediate pressure turbine (a rotary
machine) T1 according to a first embodiment of the invention, and a
meridian cross-sectional view including the axis P of the high and
intermediate pressure turbine T1. Furthermore, in the following
description, the extension direction of the axis P is referred to
as the turbine axial direction (the axial direction), the
circumferential direction of the axis P is referred to as the
turbine circumferential direction, and the radial direction of the
axis P is referred to as the turbine radial direction.
[0042] As shown in FIG. 1, in the high and intermediate pressure
turbine T1, a high pressure turbine (a rotary machine) 1A is
installed at one side of the turbine axial direction, and an
intermediate pressure turbine (a rotary machine) 1B is installed at
the other side of the turbine axial direction.
[0043] The high and intermediate pressure turbine T1 includes a
rotor 10 and a stator 50.
[0044] The rotor 10 includes a shaft body 11 which is rotatably
supported and a plurality of rotor vane rows 12 (12A and 12B) which
are formed in the shaft body 11.
[0045] The shaft body 11 penetrates the stator 50 in the turbine
axial direction, and both ends in the turbine axial direction are
supported by bearing units 91 and 92 which are disposed outside the
stator 50. The other configurations of the shaft body 11 will be
described in detail.
[0046] The plurality of rotor vane rows 12 (12A and 12B) are formed
in a manner such that a plurality of rotor vanes restrained in the
outer periphery of the shaft body 11 is arranged in the turbine
circumferential direction. The plurality of rotor vane rows 12A is
arranged in the high pressure turbine 1A, and the plurality of
rotor vane rows 12B is arranged in the intermediate pressure
turbine 1B.
[0047] The stator 50 includes an external casing 60, an internal
casing 70 (70A and 70B), and a stator vane row 52 (52A and
52B).
[0048] The external casing 60 includes an interior wall 60a which
defines an internal space 61 at the outside and a partition wall
60b which divides the internal space 61 into two parts in the
turbine axial direction. The partition wall 60b is disposed
substantially at the center of the internal space 61 in the turbine
axial direction, and divides the internal space 61 into a high
pressure turbine chamber 61A which is disposed at one side in the
turbine axial direction and an intermediate pressure turbine
chamber 61B which is disposed at the other side in the turbine
axial direction.
[0049] In the high pressure turbine 1A, the interior wall 60a of
the external casing 60 is provided with a plurality of injection
nozzles 63A which is formed at the other side in the turbine axial
direction and a discharging nozzle 64A which is formed at one side
in the turbine axial direction. Further, in the intermediate
pressure turbine 1B, the interior wall 60a is provided with a
plurality of injection nozzles 63B which is formed at one side in
the turbine axial direction and a discharging nozzle 64B which is
formed at the other side in the turbine axial direction.
[0050] A rotor 10 is inserted through the external casing 60, and
both ends of the rotor 10 (the shaft body 11) protrude from both
ends of the interior wall 60a in the turbine axial direction.
[0051] Furthermore, the gaps which are formed between the interior
wall 60a and both ends of the rotor 10 are sealed by sealing units
93A and 93B. Further, the gaps which are formed between the
partition wall 60b and the center of the rotor 10 are sealed by
sealing members 94A and 94B.
[0052] The internal casing 70 (70A and 70B) is a cylindrical member
of which both ends are opened, and which includes a stator vane
holding ring 71 which holds the stator vane row 52 (52A and 52B) in
the inner peripheral portion.
[0053] The internal casing 70A is disposed in the high pressure
turbine 1A, and the internal casing 70B is disposed in the
intermediate pressure turbine 1B. The internal casings 70A and 70B
are restrained by the inner wall of the interior wall 60a and the
partition wall 60b of the external casing 60. The internal casings
70A and 70B are inserted through the rotor 10 so as to surround the
outer periphery 10a of the rotor 10, and an annular passageway (a
passageway) 3 (3A and 3B) extends in the turbine axial direction
between the outer periphery 10a of the rotor 10 and the stator vane
holding ring 71.
[0054] The other end opening portion at the other side of the
internal casing 70A in the turbine axial direction abuts on the
partition wall 60b so as to be blocked and the gap between the
other end opening portion and the rotor 10 is sealed by the seal
member 94A.
[0055] The other end opening portion of the internal casing 70A
defines a manifold (a hydraulic fluid injection portion) 3a which
extends in the turbine circumferential direction and communicates
with the annular passageway 3 between the sealing member 94A and
the outer periphery of the shaft body 11. The manifold 3a
communicates with a connecting pipe 80A which is inserted into each
injection nozzle 63A and is air-tightly connected to the internal
casing 70A, and high pressure steam (hydraulic fluid) S1 (about
700.degree. C.) is supplied from a boiler B through the connecting
pipe 80A. The manifold 3a introduces the high pressure steam S1
into the annular passageway 3 and the high pressure steam S1
supplied to the high pressure turbine 1A first contacts the rotor
10 in the manifold 3a. That is, in the running high pressure
turbine 1A, the portion where the manifold 3a is exposed is the
hottest among the portions of the rotor 10.
[0056] Furthermore, one end opening portion of the internal casing
70A is opened toward one side in the turbine axial direction.
[0057] The opening portions of both ends of the internal casing 70B
are each opened in the turbine axial direction. A flange portion
70a, which extends in a flange shape from the outer peripheral
portion of the internal casing 70, is formed at one side of the
internal casing 70B in the turbine axial direction, and the flange
portion 70a is connected to the inner wall of the interior wall
60a, so that a manifold 3b is defined around the one end opening
portion. Intermediate pressure steam (hydraulic fluid) S2 (about
700.degree. C.) is supplied from the boiler B to the manifold 3b
through a connecting pipe 80B which is inserted to each injection
nozzle 63B.
[0058] On the other hand, in the internal casing 70B, one side of
the shaft body 11 in the turbine axial direction is covered by the
sealing member 94B. That is, the intermediate pressure steam S2
which is supplied to the manifold 3b is introduced into the annular
passageway 3B along the sealing member 94B, and the exposure
portion (the hydraulic fluid injection portion) 3c from the sealing
member 94B in the rotor 10 becomes a portion where the intermediate
pressure steam S2 first contacts. That is, in the running
intermediate pressure turbine 1B, the exposure portion 3c from the
sealing member 94B becomes the hottest among the portions of the
rotor 10.
[0059] The plurality of stator vane rows 52 (52A and 52B) is formed
in a manner such that the stator vanes restrained in the stator
vane holding ring 71 of the internal casing 70 (70A and 70B) are
arranged in the turbine circumferential direction.
[0060] The stator vane row 52A and the rotor vane row 12A are
alternately arranged from the other side in the turbine axial
direction toward one side in the annular passageway 3A of the high
pressure turbine 1A. The stator vane row 52B and the rotor vane row
12B are alternately arranged from one side in the turbine axial
direction toward the other side in the annular passageway 3B of the
intermediate pressure turbine 1B.
[0061] FIG. 2 is an enlarged cross-sectional view illustrating the
shaft body 11.
[0062] As shown in FIG. 2, the shaft body 11 is formed by joining
the rotor members 20, 30, and 40 to each other in the turbine axial
direction. More specifically, the rotor members 20, 30, and 40 are
joined to each other in the above-described order while each axis
overlaps the axis P so as to be formed in a shaft shape as a
whole.
[0063] The rotor member (the second rotor member) 20 includes a
small diameter portion 21 which is formed with a relatively small
diameter and a large diameter portion 22 which is formed with a
relatively large diameter.
[0064] In the large diameter portion 22, one end portion 20a at one
side in the turbine axial direction is depressed in a dish shape,
and the other end portion 20b is connected to, for example, the end
portion of the rotor R.sub.L of the low pressure turbine (see FIG.
1).
[0065] The rotor member (the second rotor member) 40 includes a
small diameter portion 41 which is formed with a relatively small
diameter and a large diameter portion 42 which is formed with a
relatively large diameter.
[0066] In the rotor member 40, the other end portion 40b at the
other side of the rotor member 40 in the turbine axial direction is
depressed in a dish shape, and one end portion 40a is connected to,
for example, the end portion of the rotor R.sub.VH of the ultra
high pressure turbine (see FIG. 1).
[0067] The rotor members 20 and 40 are formed of, for example, high
Cr-steel and are formed by, for example, forging. As the high
Cr-steel, for example, the compositions of 1-1 and 1-2 shown in
Table 1 below may be preferably used. In the high Cr-steel with
such a composition, the average linear expansion coefficient from
room temperature to 700.degree. C. is approximately from
11.2.times.10.sup.-6/.degree. C. to 12.4.times.10.sup.-6.degree.
C.
[0068] Furthermore, high Cr-steel with a composition other than
that in Table 1 may also be used.
[0069] Furthermore, % in Table 1 indicates the weight %.
[0070] In the rotor member (the first rotor member) 30, both end
portions (the joint end portion) 30a and 30b in the turbine axial
direction are depressed in a dish shape.
[0071] The rotor member 30 is formed of a Ni-based alloy, and has
comparatively low thermal conductivity and a high linear expansion
coefficient. As the Ni-based alloy, for example, the compositions
of 2-1, 2-2, 2-3, 2-4, 2-5, and 2-6 shown in Table 2 below may be
preferably used. In the Ni-based alloys with such compositions, the
average linear expansion coefficient from room temperature to
700.degree. C. is approximately from 12.4.times.10.sup.-6/.degree.
C. to 14.5.times.10.sup.-6.degree. C., and is suppressed so as to
be lower than that of Ni-based alloys with other compositions.
[0072] Furthermore, Ni-based alloy with a composition other those
in than Table 2 may also be used.
[0073] Furthermore, % in Table 2 indicates the weight %.
[0074] One end portion 30a of the rotor member 30 is joined to the
other end portion 40b of the rotor member 40 by welding in an
abutting state. Further, the other end portion 30b of the rotor
member 30 is joined to one end portion 20a of the rotor member 20
by welding in an abutting state.
[0075] With regard to the joint portions of both end portions 30a
and 30b of the rotor member 30 in the turbine axial direction, it
is desirable that the thickness d be set as small as possible on
the condition that the necessary strength is ensured while
maintaining the running state of the high and intermediate pressure
turbine T1.
[0076] As shown in FIG. 2, the inside of the rotor member 30 is
formed so as to be hollow. More specifically, a hole 31 with a
constant inner diameter D1 extends in the turbine axial direction
on the axis P, and one end portion 30a and the other end portion
30b communicate with each other. That is, the thermal capacity of
the rotor member 30 becomes smaller than that of the case where the
rotor member 30 is solid (i.e., the case where the hole 31 is not
formed).
[0077] The thickness of the rotor member 30 is formed so that the
center portion in the turbine axial direction is greater than or
equal to each thickness d of both end portions in the turbine axial
direction and the value of the ratio of the inner diameter D1 with
respect to the outer diameter D2 at the center portion in the
turbine axial direction is greater than or equal to 1/2.
[0078] Subsequently, operation of the high and intermediate
pressure turbine T1 with the above-described configuration will be
described with reference to the drawings.
[0079] First, when the high and intermediate pressure turbine T1 is
started up, the high pressure steam S1 flows into the high pressure
turbine 1A and the intermediate pressure steam S2 flows into the
intermediate pressure turbine 1B.
[0080] As shown in FIG. 1, for example, in the high pressure
turbine 1A, the high pressure steam S1 which passes through the
ultra high pressure turbine (not shown) and is reheated by the
boiler B is supplied to the manifold 3a through the connecting pipe
80A. Then, the high pressure steam S1 is introduced into the
annular passageway 3A along the rotor member 30, and sequentially
flows through the rotor vane row 12A and the stator vane row 52A,
thereby applying rotational force to the rotor 10. The high
pressure steam S1 which passes through the annular passageway 3A is
discharged from the high pressure turbine 1A through the discharge
nozzle 64A and sent to the boiler B.
[0081] On the other hand, for example, in the intermediate pressure
turbine 1B, the intermediate pressure steam S2 which is discharged
from the high pressure turbine 1A and is reheated by the boiler B
is supplied to the manifold 3b through the connecting pipe 80B.
[0082] Then, the intermediate pressure steam S2 is introduced from
the manifold 3b into the annular passageway 3B along the sealing
member 94B, and sequentially flows through the rotor vane row 12B
and the stator vane row 52B in the annular passageway 3B, thereby
applying rotational force to the rotor 10. The intermediate
pressure steam S2 which passes through the annular passageway 3B is
discharged from the intermediate pressure turbine 1B through the
discharge nozzle 64B and sent to the boiler (not shown).
[0083] At this time, since the inside of the rotor member 30 in the
rotor 10 is formed so as to be hollow so that the thermal capacity
is small, it is difficult for a difference in temperature between
the outside and the inside in the inner portion (more specifically,
the thick portion) of the rotor member 30 to arise.
[0084] In other words, since the rotor member 30 is formed so as to
be hollow, the distance of the thermal transmission path from the
outer peripheral end of the rotor member 30 to the inner peripheral
end thereof is shorter than that of the case where the rotor member
30 is solid, and the heat which is transmitted from the high
pressure steam S1 to the outer peripheral end of the rotor member
30 is rapidly conducted (reaches) to the inner peripheral end of
the rotor member 30. For this reason, the temperature gradient in
the turbine radial direction inside the rotor member 30 is gentle,
and the temperatures of the outside and the inside of the inner
portion of the rotor member 30 are equal to each other.
[0085] A difference in the thermal growth between the outside and
the inside of the rotor member 30 decreases in proportion to a
difference in the temperature which is generated outside and inside
of the inner portion of the rotor member 30. For this reason, it is
possible to largely suppress the thermal stress which is generated
inside the rotor member 30.
[0086] When this state is continued, the temperature of the entire
rotor member 30 increases to the running temperature of the high
and intermediate pressure turbine T1.
[0087] Then, the high and intermediate pressure turbine T1 changes
from the start-up state to the normal state. After changing to the
normal state, the rotor member 30 rotates after the temperature
becomes constant.
[0088] As described above, according to the high and intermediate
pressure turbine T1, since the inside of the rotor member 30 which
is formed of the Ni-based alloy is formed so as to be hollow
throughout the entire length in the turbine axial direction, the
thermal capacity of the rotor member 30 becomes smaller than that
of the case where the inside is solid. Accordingly, when the high
and intermediate pressure turbine T1 is rapidly started up, a
difference in the temperature which is generated between the
outside and the inside of the inner portion of the rotor member 30
is suppressed, and the temperature of the rotor member 30 increases
as a whole. Accordingly, it is possible to suppress the thermal
stress which is generated inside the rotor member 30. Thus, the
high and intermediate pressure turbine T1 may be rapidly started up
and the thermal stress generated in the rotor 10 may be
suppressed.
[0089] Further, since the shaft body 11 is adjacent to the rotor
member 30 in the turbine axial direction and the rotor members 20
and 40 which are formed of high Cr-steel are provided, it is
possible to suppress the cost of the rotor 10 compared to the case
where the entire shaft body 11 is formed of Ni-based alloy.
Furthermore, since part of the shaft body 11 is formed of high
Cr-steel which is more easily molded than the Ni-based alloy, the
rotor 10 may be easily manufactured.
[0090] Further, since the rotor member 30 is formed of Ni-based
alloy with the composition shown in Table 2, the average linear
expansion coefficient from room temperature to 700.degree. C.
becomes smaller than that of Ni-based alloy with other
compositions. Accordingly, since thermal growth hardly occurs in
the rotor member 30 compared to Ni-based alloys with other
compositions, it is possible to further suppress the thermal stress
which is generated inside the rotor member 30.
[0091] Further, since the rotor members 20 and 40 are formed of
high Cr-steel with the composition shown in Table 1 and the rotor
member 30 is formed of Ni-based alloy with the composition shown in
Table 2, a difference in the linear expansion coefficient is
decreased. Accordingly, it is possible to ensure the strength of
the joint portions of the rotor members 20 and 40 and the rotor
member 30.
[0092] Further, the thickness of the rotor member 30 is formed so
as to be greater than or equal to 1/2 of the value of the ratio of
the inner diameter D1 with respect to the outer diameter D2 at the
center portion in the turbine axial direction. Thus, it is possible
to further suppress a difference in the temperature which is
generated between the outside and the inside of the inner portion
of the rotor member 30, and further suppress the thermal stress
which is generated inside the rotor member 30. Further, the
thickness of the rotor member 30 is formed so as to be greater than
or equal to 1/2 of the value of the ratio of the inner diameter D1
with respect to the outer diameter D2 at the center portion in the
turbine axial direction. Thus, it is possible to further suppress a
difference in the temperature which is generated between the
outside and the inside of the inner portion of the rotor member 30,
and further suppress the thermal stress which is generated inside
the rotor member 30. Further, the thickness of the rotor member 30
is formed so as to be greater than or equal to thickness d of both
end portions in the turbine axial direction at the center portion
in the turbine axial direction. Thus, it is possible to ensure the
strength which is necessary for the rotor member 30.
[0093] Furthermore, since the high and intermediate pressure
turbine T1 according to the invention includes the rotor 10, even
when Ni-based alloy is used at steam conditions of 700.degree. C.
or more, the high and intermediate pressure turbine T1 may be
rapidly started up and the thermal stress generated in the rotor 10
is suppressed. Accordingly, satisfactory running performance may be
obtained, and the breakage of the rotor 10 may be prevented. Then,
since the steam S1 and the steam S2 are set to a comparatively high
temperature (about 700.degree. C.), a demand for the reduction in
the discharge amount of CO.sub.2 or the further improvement in the
thermal coefficient may be sufficiently handled.
Second Embodiment
[0094] Hereinafter, a second embodiment of the invention will be
described by referring to the drawings. Furthermore, in the
following description and the drawings used for the description,
the same reference numerals will be given to the same components as
the components described above, and the repetitive descriptions
thereof will not be repeated.
[0095] FIG. 3 is an enlarged cross-sectional view illustrating a
shaft body 11A in a high and intermediate pressure turbine (the
rotary machine) T2 according to the second embodiment of the
invention.
[0096] Compared to the configuration in which the shaft body 11 of
the first embodiment includes the rotor member 30 which is
integrally formed with the shaft body, as shown in FIG. 3, the
shaft body 11A of the high and intermediate pressure turbine T2
according to this embodiment has a configuration in which rotor
members (first rotor members) 32A and 32B are disposed at a
position corresponding to the rotor member 30.
[0097] The rotor members 32A and 32B are formed of Ni-based alloy
as in the case of the rotor member 30, and both end portions (joint
end portions) 32a, 32b, 32c, and 32d are each depressed in a dish
shape in the turbine axial direction. The inside of each of the
rotor members 32A and 32B is formed so as to be hollow.
[0098] One end portion 32a of the rotor member 32A is joined to the
other end portion 40b of the rotor member 40 (added since it is not
shown) by welding in an abutting state.
[0099] One end portion 32d of the rotor member 32B is joined to one
end portion 20a of the rotor member 20 (added since it is not
shown) by welding in an abutting state.
[0100] Further, the other end portion 32b of the rotor member 32A
and the other end portion 32c of the rotor member 32B are joined to
each other by welding (common welding) in an abutting state.
[0101] In the rotor member 32A, a hole 31A with a constant inner
diameter D1 extends in the turbine axial direction on the axis P.
In the rotor member 32B, a hole 31B with a constant inner diameter
D3 (.noteq.the inner diameter D1) extends in the turbine axial
direction on the axis P.
[0102] That is, the rotor members 32A and 32B are formed so as to
have different inner diameters.
[0103] According to the high and intermediate pressure turbine T2,
it is possible to obtain the main advantage of the first
embodiment. Further, since the inner diameters (D1.noteq.D3) are
different from each other in the manifold 3a and the exposure
portion 3c shown in FIG. 1, it is possible to adjust each
temperature distribution of the manifold 3a and the exposure
portion 3c (the high pressure turbine 1A and the intermediate
pressure turbine 1B).
[0104] Furthermore, it is possible to obtain the main advantage of
the first embodiment even when the rotor members 32A and 32B have
the same inner diameter.
Third Embodiment
[0105] Hereinafter, a third embodiment of the invention will be
described by referring to the drawings. Furthermore, in the
following description and the drawings used for the description,
the same reference numerals will be given to the same components as
the components described above, and the repetitive descriptions
thereof will not be repeated.
[0106] FIG. 4 is an enlarged cross-sectional view illustrating a
shaft body 11B in a high and intermediate pressure turbine (the
rotary machine) T3 according to the third embodiment of the
invention.
[0107] Compared to the configuration in which the shaft body 11A of
the second embodiment includes the rotor member 32B with the hole
31B, as shown in FIG. 4, a shaft body 11B of the high and
intermediate pressure turbine T3 according to this embodiment
includes a solid rotor member 33 instead of the rotor member
32B.
[0108] The rotor member 33 is formed of an Ni-based alloy, where
one end portion (the joint end portion) 33a is joined to the other
end portion 32b of the rotor member 32A by welding in an abutting
state and the other end portion 33b is joined to one end portion
20a of the rotor member 20 (added since it is not shown in the
drawings) by welding in an abutting state.
[0109] According to the high and intermediate pressure turbine T3,
it is possible to obtain the main advantages of the first
embodiment and the second embodiment in the rotor member 32A.
Further, since the inside of the rotor member 33 is solid, it is
possible to improve the rigidity of the rotor member 33 in the
intermediate pressure turbine 1B.
[0110] Furthermore, the inside of the rotor member 33 may be hollow
(as in the case of the rotor member 32B), and the inside of the
rotor member 32A may be formed so as to be solid.
Fourth Embodiment
[0111] Hereinafter, a fourth embodiment of the invention will be
described by referring to the drawings. Furthermore, in the
following description and the drawings used for the description,
the same reference numerals will be given to the same components as
the components described above, and the repetitive descriptions
thereof will not be repeated.
[0112] FIG. 5 is an enlarged cross-sectional view illustrating a
shaft body 11C in a high and intermediate pressure turbine (the
rotary machine) T4 according to the fourth embodiment of the
invention.
[0113] Compared to the configuration in which the shaft body 11A of
the second embodiment includes the rotor members 32A and 32B having
the holes 31A and 31B with constant inner diameters D1 and D3, as
shown in FIG. 5, a shaft body 11C of the high and intermediate
pressure turbine T4 according to this embodiment includes rotor
members (first rotor members) 34A and 34B in which the inner
diameters of the holes 35A and 35B respectively formed therein are
different at each portion in the turbine axial direction.
[0114] The hole 35A of the rotor member 34A is formed in, for
example, a tapered shape in which the inner diameter gradually
decreases toward one end side of the rotor member 34A from the
other end side in the turbine axial direction.
[0115] The hole 35B of the rotor member 34B is formed in, for
example, a tapered shape in which the inner diameter gradually
decreases from one end side of the rotor member toward the other
end side in the turbine axial direction.
[0116] According to the high and intermediate pressure turbine T4,
it is possible to obtain the main advantages of the first
embodiment and the second embodiment. Further, since the inner
diameters (the holes 35A and 35B) of the rotor members 34A and 34B
are different at each portion in the turbine axial direction, it is
possible to adjust the temperatures of the rotor members 34A and
34B (the high pressure turbine 1A and the intermediate pressure
turbine 1B) in the turbine axial direction.
[0117] Furthermore, in the embodiment, the hole 35A is formed in a
tapered shape in which the inner diameter gradually decreases from
one end side of the rotor member 34A toward the other end side in
the turbine axial direction, but may be formed so that the inner
diameter gradually decreases toward one end side of the rotor
member 34A from the other end side in the turbine axial direction.
Further, a part of the hole 35A may have a portion with a constant
inner diameter. Further, a portion may be formed in which the inner
diameter of the hole 35A increases and then decreases in the
turbine axial direction. The same applies to the hole 35B.
[0118] Further, as in this embodiment, the inner diameter of each
hole of the first embodiment to the third embodiment may be changed
in the turbine axial direction.
[0119] Furthermore, the operation sequences or all shapes,
combinations, and the like of the components shown in the
above-described embodiments are examples, and may be modified into
various forms based on the design requirements and the like in the
scope without departing from the spirit of the invention.
[0120] For example, in the above-described embodiments, each end
portion of the rotor members 20, 30, 40, 32A, 32B, 33, 34A, and 34B
in the turbine axial direction is formed in a dish shape, but may
be depressed in other shapes in the turbine axial direction.
Further, the end portion may be formed in a flat shape without
being depressed in the turbine axial direction.
[0121] Further, in the above-described embodiments, a case has been
described in which the invention is applied to the high and
intermediate pressure turbines T1 to T4, but the invention may be
applied to the turbine of another pressure range. Further, the
invention may be applied to a rotary machine other than a
turbine.
INDUSTRIAL APPLICABILITY
[0122] According to the rotor of the rotary machine of the
invention, it is possible to rapidly start-up the rotary machine
and suppress the thermal stress generated in the rotor.
DESCRIPTION OF REFERENCE NUMERALS
[0123] 1A: high pressure turbine (rotary machine)
[0124] 1B: intermediate pressure turbine (rotary machine)
[0125] 3 (3A and 3B): annular passageway (passageway)
[0126] 3a: manifold (hydraulic fluid injection portion)
[0127] 3c: exposure portion (hydraulic fluid injection portion)
[0128] 10: rotor
[0129] 10a: outer periphery
[0130] 20: rotor member (second rotor member)
[0131] 30: rotor member (first rotor member)
[0132] 30a and 30b: both end portions (joint end portion)
[0133] 32A and 32B: rotor member (first rotor member)
[0134] 32a, 32b: both end portions (joint end portion)
[0135] 32c, 32d: both end portions (joint end portion)
[0136] 33: rotor member (first rotor member)
[0137] 33a: one end portion (joint end portion)
[0138] 34A: rotor member (first rotor member)
[0139] 34B: rotor member (first rotor member)
[0140] 40: rotor member (second rotor member)
[0141] 50: stator
[0142] P: axis
[0143] D: thickness
[0144] D1, D3: inner diameter
[0145] D2: outer diameter
[0146] S1: high pressure steam (hydraulic fluid)
[0147] S2: intermediate pressure steam (hydraulic fluid)
[0148] T1, T2, T3, T4: high and intermediate pressure turbine
(rotary machine)
* * * * *