TURBINE NOZZLE AND MANUFACTURING METHOD THEREOF
5 Technical Field
[0001]
The present invention relates to a turbine nozzle
and a manufacturing method thereof, and more
particularLy to the turbine nozzle that is a component
10 of a turbo pump of a rocket engine and the
manufacturing method thereof.
Background Art
[0002]
15 In a rocket engine, a turbo pump is used in
supplying fuel or oxidizing agent (See Patent
Literature 1). As one of components of the turbo pump,
there is a turbine nozzle. The turbine nozzle is the
component which expands and decompresses a gas, and
20 changes a gas flow direction such that the gas
impinges a turbine blade at the optimum angle.
Citation List
/5 [Patent Literature]
[0003]
30
Patent Literature 1: Japan Patent Application
Publication JP 2009-222010 A
Summary of the Invention
[0004]
Traditionally, the turbine nozzle was
integrally formed as one piece. Note that if a
smaller sized turbine nozzle is required, a
35 manufacturing method thereof is limited because it is
difficult to make a narrow flow passage by machining.
- 2 -
However, if, for example, electrical discharge
machining is used, there exists a problem that
manufacturing costs and manufacturing time increase.
If molding is used, there exist problems that the
5 manufacturing time increases and manufacturing costs
relatively becomes high for small-quantity production.
[0005]
One object of the present invention is
providing a technique with which manufacturing costs
10 and manufacturing time of a turbine nozzle can be
reduced.
[0006]
ln one aspect of the present invention, a
manufacturing method of a turbine nozzle is provided.
15 The turbine nozzle includes an inner ring portion, an
outer ring portion having a diameter larger than a
diameter of the inner ring portion, and a blade (a
vane) arranged between the inner ring portion and Lhc
outer ring portion. The manufacturing method includes:
20 (A) forming a first part which includes the blade and
one of the inner ring portion and the outer ring
portion integrated therein; (B) forming the other of
the inner ring portion and the outer ring portion as a
second part; (C) combining the first part and the
25 second part such that an outer side surface of the
inner ring portion and an inner side surface of the
outer ring portion are arranged to oppose each other
and that a gap is formed between the blade of the
first part: and the second part; and (D) flowing a
30 brazing material in a molten state into the gap to
braze the blade of the first part and the second part.
[0007]
The manufacturing method may further include:
inserting a spacer in the gap between the above-
35 mentioned step (C) and the above-mentioned step (D)
[0008]
5
- 3 -
The brazing material may be arranged at a
position adjacent to the gap on an upper surface of
the blade.
[0009]
The brazing material may include both a wire
type brazing material and a powder type brazing
material.
[ 0 010 J
Preferably, the first part includes the inner
10 ring portion and the blade integrated therein. On the
other hand, the second part is the outer ring portion.
[ o o 11 I
ln another aspect of the present invention, a
turbine nozzle is provided. The turbine nozzle
15 includes: an inner ring portion; an outer ring portion
having a diameter larger than a diameter of the inner
ring portion; and a blade (a vane) arranged between
the inner ring portion and the outer ring portion.
20
25
The blade and one of the inner ring portion and the
outer
part.
outer
first
[0012]
ring portion are integrally formed as a first
The other of the inner ring portion and the
ring portion constitutes a second part. The
part and the second part are joined by brazing.
According to the present invention, it lS
possible to reduce the manufacturing costs and
manufacturing time of the turbine nozzle.
Brief Description of the Drawings
30 [0013]
Fig. 1 is a plan view for schematically
indicating a configuration of the turbine nozzle;
Fig. 2 is a side view for schematically
indicating a cross-sectional structure of a blade of
35 the turbine nozzle;
Fi_g. 3 is a plan view for schematically
- 4
indicating a manufacturing method of the turbine
nozzle according to the first embodiment;
Fig. 4 is a plan view for explaining the
manufacturing method of the turbine nozzle according
5 to the ficst embodiment;
Fig. 5 is a side view for explaining the
manufacturing method of the turbine nozzle according
to the first embodiment;
Fig. 6 is a plan view for explaining the
10 manufacturing method of the turbine nozzle according
to the second embodiment;
Fig. 7 is a side view for explaining the
manufacturing method of the turbine nozzle according
to the second embodiment;
15 Fig. 8 is a side view for explaining the
manufacturing method of the turbine nozzle according
to the third embodiment; and
Fig. 9 is a plan view for schematically
indicating the manufacturing method of the turbine
?0 nozzle according to the fourth embodiment.
Description of Embodiments
[0014]
Reference to the accompanying drawings, a
25 turbine nozzle according to some embodiments will be
explained.
[00151
(First embodiment)
FLG. l is the plan view for schematically
30 indicating the turbine nozzle 1 according to the
present embodiment. The turbine nozzle 1 includes an
inner ring portion 10, an outer ring portion 20, and a
blade 30 (blades 30).
35
roo 16 J
I< a c h o f t h e i n n e r r i n g p o r t i o n 1 0 a n d t h e o u t e r
ring portion /.0 is a member having a ring shape. The
5
- 5
inner ring portion 10 has an inner side surface 11 and
an outer side surface 12. The outer ring portion 20
has an inner side
22. !\ diamcte;r of
than a d i arne; te r of
surface 21 and
the outer ring
the inner ring
an outer
portion
portion
side surface;
20 is larger
10. More
specifically, the diameter of the inner side surface
21 of the outer ring portion 20 is larger than the
diameter of the outer side surface 12 of the inner
ring portion 10. Thus, it is possible to place the
10 inner ring portion 10 inside a ring of the outer ring
portion 20 such that the outer side surface 12 of the
inner ring portion 10 and the inner side surface 21 of
the outer ring portion 20 are arranged to oppose each
other.
15 [0017]
The blades 30 are positioned between the inner
ring portion 10 and the outer ring portion 20. Fig. 7
schematically indicates the cross-sectional structure
of the blades 30 when viewed along the direction A
20 shown in Fiq. 1. As shown in Fig. 2, each blade 3C
has a cross-sectional shape of a cross-sectional
airfoil shape. Then, as shown in Fig. 1, a plurality
of blades 30 is arranged annularly in a space between
the inner ring portion 10 and the outer ring portion
25 20. A gap between adjacent blades 30 is served as a
gas fJow passage.
roo 1 a 1
If a more compact turbine nozzle is required,
the gas flow passage also becomes narrow. When the
30 turbine noz7.le is integrally formed as a one piece, i l
is difficult to make precisely such a narrow gas flow
passage by machining. Therefore, in the present
embodimcn t, a new manu fact uri ng method as shown in 1·' i q.
3 Ls proposed.
[0019]
6 -
Firstly, a first part PA and a second part PB
are separately formed. The first part PA is a part
which integrally includes the inner ring portion 10
and a blade 30 (blades 30). On the othE;r hand, the
~ second part PB is the outer ring portion 20. In
forming the first part PA, it is not required to form
a through hole of complex shape in order to form the
gas flow passage and the blade 30 may be formed by
processing a surface exposed to outside. That is, it
10 is possible to apply a machining to form the first
par-t PJ\.
[0020]
Subsequently, the first part PA is arranged
inside a r-ing of the second part PB (the outer ring
15 portion 20). That is, the first part PA and the
second part PB are combined such that the outer side
surface 12 of the inner ring portion 10 and the inner
side surface 21 of the outer ring portion 20 are
arr-anged to oppose each other. Then, the blades 30 of
20 the first part PA and the second part PB are joined by
"brazing". In this way, the turbine nozzle 1 is
completed. 'rhe turbine nozzle 1 manufactured in this
way has a brazed portion 40 (a joint portion formed of
a brazing material) between the blade 30 and the
2:) second parL PB.
[00/.1]
l·' i q . t1 and Fig . 5 a r e the p l an v i e w and t he
side view, respectively for explaining the abovementioned
"blazing" in more detail. When the first
30 part PA is disposed inside the ring of the second parL
PB (the outer ring portion 20), a small gap 50 is
formed between the blade 30 and the inner side surface
21 of Lhc second part PB (the outer ring portion 20)
as shown in Fig. 4. In other words, a size and shape
35 of the first part PA and the second part PB is
designed so that the small gap 50 can be formed.
- 7
Although it is preferred that the gap is constant, it
is not limited thereto. By melting the brazing
material 60 and flowing the molten brazing materia] 60
into the gap 50, the blade 30 of the first part PA and
S the second part PB are brazed.
[ 0 0 2 2 l
The brazing material 60 is a metal alloy having
lower melting point than the first part PA and the
second part PR, which are base members. For example,
10 a nickel-based brazing material 60 can be used. Such
a brazing material 60 is arranged in the gap 50 or the
vicinity thereof. Typically, since the gap SO is very
narrow, the brazing material 60 is placed at a
position, on the upper surface of the blade 30,
15 adjacent to the gap SO as shown in Fig. 4 and Fig. 5.
After the arrangement of the brazing material 60,
heating is performed. By the heating, the brazing
material 60 Ls molten, and the molten brazing material
flows into the gap SO. In this way, the blade 30 of
20 the first part PA and the second part PB are brazed.
[0023]
As expJained above, according to the present
embodiment, the turbine nozzle 1 is manufactured by
brazing the first part PA and the second part PB. fn
75 the case in which the turbine nozzle is downsized, the
gas passage also becomes narrow. In the case in which
the turbine nozzle 1 is integrally formed as the one
piece, it is difficult to make precisely such a narrow
gas fJow passage by machining. On the other hand,
30 according to the present embodiment, the first part PA
and the second part PB can be easily made by machining.
Therefore, as compared with the case of electrica1
discharge machining or casting, it is possible to
reduce the costs and time for manufacturing the
35 turbine nozzle 1.
[00/~]
- 8 -
(Second embodiment)
F'iq. 6 and Fig. 7 are the plan view and the
sLde view, respectively for explaining the blazing
according to the second embodiment. As described
5 above, when the first part PA is disposed inside the
ring of the second part PB, the small gap 50 is formed.
Therefore, after brazing, "misalignment" between the
first part PA and the second part PB is likely to
occur. To prevent the occurrence of such misalignment,
1 0 a s p a c e r ·; 0 ( s p a c e r s 7 0 ) i s i n s e r t e d i n t o t h e g a p 5 0
according to the second embodiment. After the
insertion of the spacer 70 into the gap 50, as in the
first embodiment, the brazing material 60 is molten
and the molten brazing material is flown into the qap
1 5 50.
[002~l]
1\s the spacer 70, a nickel foil can be
exempJiiLed. Such a spacer 70 is arranged between the
outer side surface of the blade 30 and the inner side
20 surface 21 of the outer ring portion 20. Installation
position of the spacer 70 is arbitrary so long as the
occurrence of the misalignment can be prevented.
However, it is preferable that the spacers 70 are
evenly spaced over the entire circumference of the gap
25 50.
[00261
According to the second embodiment, the same
effect as the first embodiment can be obtained. [n
addition, the "misalignment" between the first part PI30 and the second part PB is prevented from occurring.
[002'/]
(Third embodiment)
FLq. tl is the schematic diagram for explainLnq
the brazing material 60 according to the third
35 embodim0::nt. ln the third embodiment, the brazing
material 60 includes a powder type brazing material 62
~
- 9 -
in addition to a wire type brazing material 61. The
powder type brazing
being easily molten
material 6] Then,
material
than the
when the
62 has characteristics of
wire type brazing
powder type brazing
material 62 melts, it induces melting of the wire type
brazing material and the wire type brazing material 61
starts melting. That is, when the powder type brazing
material 62 is used, the wire type brazing material 61
lS Likely Lo easily melt as compared with the case
10 where there is no powder type brazing material 62.
lOO/.tl]
The powdered type brazing material 62 is, for
exampJe, provided in an end portion of the brazing
material 60. In the example shown in Fig. 8, the
1~ powder type brazing material 62 is applied on both
20
ends of the wire type brazing material 61. Thereby,
the brazing material 60 is likely to easily melt as a
whole.
[0029]
The combination of the second embodiment and
the third embodiment described above is possible.
[0030]
(Fourth embodiment)
1n the embodiments described above, the inner
7.5 ring portion 10 and the blade 30 are integrally formed.
1n t h e C o u r t h em b o d i me n t , a l t e r n a t i v e l y , t he o u t e r
ring portion 20 and the blade 30 are integrally formed.
Referring to Fig. 9, the manufacturing method of the
turbine nozzle according to the fourth embodiment wi I
30 be explained.
[0031]
l·' i r s L I y , the f i r s t part P A and t he s e con d p a r L
PB are separately formed. In the present embodiment,
the first part PAis a part which integrally includes
35 the outer ring portion 20 and the blade 30 (the blades
- 10 -
30). On Lhc other hand, the second part PB is the
inner ring portion 10.
[003/]
Subsequently, the second part PB (the inner
~ ring portion 10) is arranged inside the ring of the
first part PA. That is, the first part PA and the
second part PB are combined such that the outer side
surface 1? of the inner ring potion 10 and the inner
sLde surtacc 71 of the outer ring portion 20 are
10 arranged to oppose each other. Then, the blade 30 of
the first part PA and the second part PB are joined by
"brazing". The method of brazing is the same as the
aforementioned embodiments. The turbine nozzle 1
manufactured in this way has the brazed portion 40
1~ (Lhe joint portion formed of the brazing material)
between Lhe blade 30 and the second part PB.
[0033]
However, it is easier to form the blade 30 on
the outer side surface 12 of the inner ring portion 10
/0 as compared with the case where the blade 30 is formed
on the inner side surface 21 of the outer ring portLon
20. rn this sense, those of the aforementioned
embodiments is preferred than those of the fourth
embodiment.
25 [0031]
ln lhe above, some embodiments of the present
invention have been explained with reference to the
attached drawings. However, the present invention is
not Limited to the above-mentioned embodiments, and
30 they may be appropriately modified by those skilled In
the art without departing from the spirit or scope of
the general invention concept thereof.
[0035]
This application claims a priority based on
3::) Japanese Patent Application No. JP 2013-029430. The
11
disclosure of which is hereby incorporated by
reference herein in its entirely.
- 12 -
CLAIMS
1. A manufacturing method of a turbine nozzle, the
turbine nozzle including an inner ring portion, an
5 outer ring portion having a diameter larger than a
diameter of the inner ring portion and a blade
arranged between the inner ring portion and the outer
ring portion, the method comprising:
(A) forming a first part which includes the
10 blade and one of the inner ring portion and the outer
ring portion integrated therein;
20
30
35
(B) forming the other of the inner ring portion
and the outer ring portion as a second part;
(C) combining the first part and the second
part such that an outer side surface of the inner ring
portion and an inner side surface of the outer ring
portion are arranged to oppose each other and that a
gap is formed between the blade of the first part and
the second part; and
(D) flowing a brazing material in a molten
state Lnto the gap to braze the blade of the first
part and the second part.
2. The manufacturing method according to claLm 1,
further comprising:
inserting a spacer in the gap between (C) the
combinJnq the first part and the second part and (D)
the flowing a brazing material in a molten state into
the qap.
3. The manufacturing method according to claim 1
or 2, wherein the brazing material is arranged at a
posit1on adjacent to the gap on an upper surface or
the bl adc;.
4. The manufacturing method according to any one
- 13 -
of claims 1 to 3, wherein the brazing material
includes both a wire type brazing material and a
powder type brazing material.
5 5. The manufacturing method according to any one
] 0
of claims 1 to 4, wherein the first part includes the
inner ring portion and the blade integrated therein,
wherein the second part is the outer ring
portion.
6. A turbine nozzle comprising:
an inner ring portion;
an outer ring portion having a diameter larger
than a diameter of the inner ring portion; and
1~ a blade arranged between the inner ring portion
/.0
/.5
and the outer ring portion,
wherein the blade and one of the inner ring
portion and the outer ring portion are integrally
formed as a first part,
wherein the other of the inner ring portion and
th~ outer ring portion constitutes a second part, and
wherein the first part and the second part arc
joined by brazing.