U.S. patent number 3,867,063 [Application Number 05/298,631] was granted by the patent office on 1975-02-18 for stator of multistage turbomachine.
Invention is credited to Eduard Grigorievich Bulavin, Jury Evgenievich Sljusarev.
United States Patent |
3,867,063 |
Bulavin , et al. |
February 18, 1975 |
STATOR OF MULTISTAGE TURBOMACHINE
Abstract
A stator comprises a housing accommodating a guiding device for
each stage and a working ring for each stage. The guiding device
comprises an external ring and fixed blades secured to the external
ring. Working blades of the turbomachine rotate inside the working
ring. The external ring is provided with a shoulder at each end
face thereof, said shoulder being adapted to limit the radial
displacement of the working ring relative to the external ring and
extending along the circumference of the external ring. Each end
face of the working ring is provided with a groove. This groove
extends along the circumference of the working ring and encloses
the shoulder. in order to limit the circumferential displacement of
the working ring relative to the external ring, the working ring is
provided with means comprising a stud. This stud is mounted in the
working ring in such a manner that one end thereof is connected to
the external ring of the guiding device of the same stage, while
the other end is connected to the external ring of the guiding
device of the adjacent stage.
Inventors: |
Bulavin; Eduard Grigorievich
(Zaporozhie, SU), Sljusarev; Jury Evgenievich
(Zaporozhie, SU) |
Family
ID: |
25763952 |
Appl.
No.: |
05/298,631 |
Filed: |
October 18, 1972 |
Current U.S.
Class: |
415/199.5;
415/138; 415/209.3 |
Current CPC
Class: |
F01D
9/042 (20130101) |
Current International
Class: |
F01D
9/04 (20060101); F01d 001/02 (); F01d 009/00 () |
Field of
Search: |
;415/198,199R,217,218,136,137,178,138,139 ;60/39.32 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Freeh; William L.
Assistant Examiner: Casaregola; Louis J.
Attorney, Agent or Firm: Waters; Eric H.
Claims
1. A stator of a multistage turbo-machine comprising:
a housing of a turbo-machine;
a guiding device of each stage of the turbo-machine accommodated in
said housing and including an external ring and fixed blades
secured to said external ring;
a working ring of each stage fixed in said housing;
annular shoulders for limiting radial displacement of said working
ring relative to said external ring, one shoulder being made at
each end face of said external ring;
an annular groove at each end face of said working ring, said
groove enclosing said shoulder of said external ring; and
limiting means for limiting the circumferential displacement of
said working ring relative to said external ring, said limiting
means comprising:
a plurality of studs spaced along a circle, rigidly secured in each
said working ring and extending substantially axially through said
working ring, opposite ends of each stud being substantially
located in correspondence annular grooves at opposite faces of said
working ring;
a plurality of axial slots in said shoulders of said external ring,
each of said slots receiving one end of one of said studs and the
longitudinal
2. A stator according to claim 1, wherein said axial slots are
3. A stator according to claim 2, wherein each of said studs has a
diameter greater than the width of said grooves at the end faces of
said working
4. A stator according to claim 3, wherein said working ring has a
flange at either end thereof, the end of each of said studs being
rigidly embedded in the flange body.
Description
The present invention relates to the art of turbomachine building,
and more particularly to stators of multistage turbomachines.
The invention may be most advantageously used in axial compressors
and in the turbines of gas-turbine engines.
Widely known stators of multistage compressors comprise a
compressor housing accommodating working rings of a plurality of
stages, working blades rotating inside the rings, and guiding
devices of the same stages having fixed blades connected to the
external rings thereof. In this embodiment, guiding devices have a
joint in the centerplane.
In the known stator, the working rings and the external rings of
the guiding devices are interconnected in such a manner that the
internal surfaces thereof form smooth outline without steps which
defines an air duct, while the external surfaces of these rings are
concentric. The external ring of the guiding device of each stage
is provided with a shoulder at each face, said shoulder extending
along the circumference of the ring. The shoulder at the end face
of that external ring, which faces the working ring of the same
stage, is formed by the prolongation of the external surface of the
ring, whereas the shoulder at the other end face of the external
ring, which faces the working ring of the adjacent stage, is formed
by the prolongation of the internal surface thereof. The working
ring of each stage is provided with a groove made at each end face,
said groove extending along the circumference of the working ring
and enclosing the shoulder.
The working rings accommodating the working blades rotating with a
small gap relative thereto are subjected to a circumferential force
due to the resistance offered by the internal surface of the ring
to the air entrained by the blades. In addition, the blades may
touch the surface of the working ring thereby producing an
additional circumferential force which is added to the
above-mentioned force and tends to rotate the ring. The rotation of
the ring will result in additional heat release due to the friction
between the ring and the stator housing, said heat release
resulting in deformation of the ring itself and of the housing,
whereby it is necessary to fix the working ring in the rotational
direction.
The guiding devices of each stage having their fixed blades located
in the zone of the moving air flow are subjected to a force which
is resultant of a total of all aerodynamic forces applied to every
blade. This force has the axial and the circumferential components.
The axial component displaces the guiding device along its
longitudinal axis, and the circumferential component rotates the
guiding device about this axis. The axial component is directed
opposite to the air flow in the compressor and in the known stator
is sequentially transmitted through all the working rings and
guiding devices from the ultimate stage to the first and further to
the compressor housing. The circumferential component, in the
example under construction, is sequentially transmitted through the
joints of the working ring of the first stage to the external ring
of the guiding device of the first stage, then to the working ring
of the second stage, and so on up to the working ring of the
ultimate stage and therefrom to the housing, the circumferential
force being transmitted progressively growing from the first stage
to the ultimate one. At the ultimate stage, this force represents a
total of all the forces applied to the working rings and the
guiding devices of every stage. The circumferential force of a
respective value is transmitted at each joint by means of studs,
each stud having one end press-fitted into one of the end faces of
the external ring of the guiding device, while the other end being
received in a hole made in the end face of the working ring.
The member of the studs in each joint is defined depending upon the
amount of the circumferential force being transmitted.
This pattern of transmission of the circumferential force between
the working rings and the external rings of the guiding devices of
each stage has the following disadvantages.
The use of double alignment at the joint between the working ring
and the external ring of the guiding device by means of the stud
and the shoulder each ensuring the alignment in all directions
results in additional stresses arising in the stud and in the point
of its fastening in the external ring of the guiding device. Since
the component parts in the joint exhibit high local rigidity, these
stresses may attain substantial value. On the other hand, the
utilization of a plurality of the studs in the joint requires
accurate arrangement thereof both in radial and circumferential
directions, as well as accurate arrangement of the holes in the
working ring, the appearance of additional assembly stresses being
otherwise possible in the studs and in the points of their
embedding for the above-mentioned reasons. This considerably
reduces reliability and durability of the stator. When the studs
and the holes are arranged with different pitch deviations, each
stud will be subjected to a different amount of the circumferential
force. Therefore, the requirement as to accurate arrangement of the
studs and holes makes this joint difficult in manufacture, whereby
the production cost of this assembly is increased.
As far as the attachment of the studs to the external ring of the
guiding device is concerned, it will be apparent that the depth of
embedding thereof is in inverse proportion to the stresses arising
in the embedded portion of the stud and in the adjoining material.
In other words, a greater width of the attachment of the studs in
the external ring of the guiding device is required in the example
under consideration, which results in an increased weight of the
stator.
Attempts were made to increase reliability and durability of the
stator by lowering stresses in the members utilized to connect the
working rings to the external rings of the guiding devices.
In this case, the stator of a multistage compressor comprises a
compressor housing accommodating working rings of a plurality of
stages, working blades rotating inside these rings, and guiding
devices of the same stages having fixed blades connected to the
external rings. In this known stator, the external rings of the
guiding devices are interconnected in such a manner that their
internal surfaces form smooth outline without steps which defines
the air duct, while the external surfaces of these rings are
concentric.
The external ring of the guiding device of each stage is provided
with projections at each end face. The working ring of each stage
is recessed at each end face. Upon coupling the working ring to the
external ring of the guiding device, a conventional axial splined
joint is formed. It is common knowledge that when the
circumferential force is transmitted through such a joint, low
stresses arise in the contact plane and at the tooth root due to a
considerable contact area of the teeth and high rigidity thereof in
the direction of the force transmission.
This stator is, however, difficult in manufacture, since the
provision of a large number of projections on one part and recesses
on the other part is labor-consuming and expensive. This fact
appears to be more important if the requirement of accurate
manufacturing of the above-mentioned members is taken into
account.
Also known in the art is a stator of a multistage compressor
comprising a compressor housing accommodating a working ring of
each stage, working blades rotating inside this ring, and a guiding
device of each stage having fixed blades. The guiding device has a
joint in the centerplane. The external of the guiding device of
each stage is provided with a groove extending along the
circumference of the external ring. The working ring of each stage
is provided with shoulder at each end face, said shoulder extending
along the circumference and being enclosed by the groove of the
external ring. This joint between the external ring of the guiding
device and the working ring allows for limiting their relative
radial displacement. The shoulder of the working ring is provided
with radial projections, and the external ring of the guiding
device is provided with radial slots which are adapted to receive
the radial projections.
This method for connecting the external ring of the guiding device
to the working ring allows for limiting the circumferential
displacement of the working ring relative to the external ring.
At the same time, these radial projections are used for aligning
the working rings in the housing.
In this case, the circumferential forces are sequentially
transmitted through the joints of the working ring of the first
stage to the external ring of the guiding device of the first
stage, then to the working ring of the second stage and so on up to
the working ring of the ultimate stage and further to the
housing.
The above-described connection between the working ring and the
external ring of the guiding device is substantially a splined
joint. It is common knowledge that in transmitting the
circumferential force through such a joint low stresses arise in
the contact plane and at the tooth root due to a considerable
contact area and high rigidity of the teeth in the direction of the
force application.
This joint between the working rings and the external rings of the
guiding devices is, however, difficult in manufacture, while the
provision of the radial projections on the shoulders of the working
rings is labor-consuming thereby resulting in high cost of the
stator. On the other hand, discontinuous contact between the
projections and the compressor housing in the presence of vibration
results in local cold hardening of the hosing surface.
It is an object of the present invention to reduce stresses in the
component parts of the stator and to improve its reliability in
operation.
Another object of the invention is to make the stator more simple
in manufacture and to reduce the production cost thereof.
A further object of the invention is to reduce the weight of the
stator.
The above and other objects of the invention are accomplished by
the provision of a stator of multistage turbomachine comprising a
housing accommodating a guiding device of each stage having fixed
blades, the external ring of the guiding device being provided with
a shoulder at each end face, said shoulder extending along the
circumference of said ring, and a working ring of each stage, said
ring being provided with means for limiting the circumferential
displacement of the working ring relative to the external ring and
accommodating working blades rotating therein, the working blades
having a groove at each end face, said groove extending along the
circumference of the working ring and enclosing the shoulder of the
external ring, wherein according to the invention, said means
comprises a stud which is mounted in the working ring in such a
manner that one end of the stud is connected to the external ring
of the guiding device of the same stage while the other end thereof
is connected to the external ring of the guiding device of the
adjacent stage.
It is advantageous that each shoulder of the external ring of the
guiding device have radial slots, the axis of each slot, which
extends in parallel with the turbine axis, being aligned with the
longitudinal axis of the stud.
It is desirable that the working ring be provided with holes
adapted to receive the studs, the longitudinal axis of each hole
extending inside each groove.
It is advisable that the diameter of the stud be slightly greater
than the width of the groove.
This embodiment of the stator ensures a reduction in stresses in
the component parts therof. This is achieved due to the fact that
the stud mounted in the working ring being received with one end in
the hole of the external ring of the guiding device of the same
stage and with the other end in the hole of the external ring of
the adjacent stage, is embedded along the entire length thereof or
at least in the zones located directly adjacent to the ends
thereof. That is, that part of the stud, which is subjected to the
force applied from the adjacent external ring of the guiding
device, is several times shorter than the length of the stud
attachment or than the distance between the points of attachment.
It is common knowledge that in this case minimum stresses will
arise both in the stud and in the hole. On the other hand, if the
stud axis extends inside the groove, and the diameter of the stud
is greater than the width of the groove, those parts of the stud,
which are subjected to the force applied from the guiding devices
are also embedded in the same working ring with two segments along
the generatrix lines in addition to the above-described attachment
of the stud. This contributes to further reduction in stress in the
stud proper and in the working ring. Since the stud is received in
the slot which is radially arranged relative to the working ring,
there are no stresses in the stud in this direction. Due to the
reduction in stresses in the component parts of the stator, its
reliability in operation is improved.
Due to such an embodiment of the stator, the manufacture thereof is
facilitated, since the drilling of the holes for the studs and the
installation of the studs are simple technological steps.
Simplified technological procedure of the manufacture of the stator
results in a reduced production cost thereof.
Furthermore, this embodiment of the stator allows for trimming its
weight, since the above-described embedding of the studs makes it
possible to minimize the thickness of the shoulders of the working
rings wherein the holes for the studs are made.
Other features and advantages of the invention will become apparent
from the following description of the embodiment thereof with
reference to the accompanying drawings wherein:
FIG. 1 schematically shows a stator of a multistage turbomachine
according to the invention in a longitudinal cross-sectional
view;
FIG. 2 is a fragmentary longitudinal cross-sectional view of the
stator according to the invention with the working ring and the
guiding device on the enlarged scale;
FIG. 3 is an enlarged sectional view taken along the line III--III
in FIG. 2.
A stator of a multistage turbo-machine, such as compressor
comprises a housing 1 (FIG. 1) accommodating a guiding device 2 of
each stage having fixed blades 3, and a working ring 4 of each
stage accommodating working blades 5 rotating therein. The guiding
device 2 has an external ring 6 provided with shoulders 7 at each
end face thereof, the shoulders extending along the circumference
of the ring 6. The working ring 4 is provided with radial shoulders
8 each having grooves 9 (FIG. 2) extending along the circumference
of the ring 4. The grooves 9 of the working ring 4 enclose the
shoulders 7 of the external ring 6 of the guiding device 2. The
shoulders 8 are provided with mutually coaxial holes 10 which
receive studs 11. The shoulders 7 are provided with radial slots 12
(FIG. 3), the axis of each slot extending in parallel with the axis
of the turbo-machine and being in alignment with the axis of the
stud 11. The studs 11 are received in these slots 12.
The housing 1 (FIG. 1) is provided with 13 for positioning the
working rings 4.
This ensures mutual arrangement of the internal surfaces of the
working rings 4 and the external rings 6 of the guiding devices 2
which define smooth boundary of the air duct.
Each guiding device 2 directly following the working ring 4 is
included in the body of the same stage as said working ring 4. Each
working ring 4 directly following the guiding device 2 is included
in the body of the next stage.
During the operation of the multistage compressor, the
circumferential forces are transmitted from the working ring 4 of
the first stage to the external ring 6 of the guiding device 2 of
the first stage, then to the working ring 4 of the second stage and
so on up to the working ring 4 of the ultimate. The working ring 4
of the ultimate stage is provided with a flange 14 which is adapted
to transmit a total circumferential force to the housing 1 of the
compressor by means of bolts 15. The circumferential force is
transmitted through the stud 11 (FIG. 3) and the surface 16 of the
slot 12 in contact with the stud 11. The studs 11 are made with the
diameter which is greater than the width of the groove 9, whereby
the stud has greater rigidity and larger bearing surface in the
working ring 4, which in combination with the fastening of the stud
11 in two points spaced apart of a substantial distance
considerably reduces stresses in the stud 11 proper and in the
adjoining material of the working ring 4. The radial slots 12 are
made wider than the stud diameter, whereby during the assembly
there are no assembly stresses in the stud 11 and in the working
ring 4, as well as in the external ring 6 of the guiding device 2
in the circumferential direction, and since the slot 12 is arranged
radially, there is no assembly stresses in the above-mentioned
members in the radial direction as well.
Since the studs 11 and the slots 12 are non-uniformly distributed
along the circumference of the rings within the range of the
manufacturing tolerances, they are differently loaded during the
transmission of the circumferential force, thereby resulting in
different stresses arising in the studs 11 and in the fastening
zones thereof.
In order to equalize stresses arising from the circumferential
forces in the studs 11 differently located along the circumference,
only one side of the slot 12, namely the working side thereof
contacting the stud 11 during the operation, should extend
precisely along the circumference. This embodiment of the slot 12
improves technological procedure of its manufacture, since it is
easy to make the slot with only one side which is to be accurately
located.
It will be apparent that all the above considerations are equally
applicable for a stator, in which the studs and the grooves are
included in the body of the external rings of the guiding devices,
while the shoulders and the holes are included in the body of the
working rings.
* * * * *