U.S. patent number 3,894,324 [Application Number 05/280,142] was granted by the patent office on 1975-07-15 for rotor for fluid flow machines.
This patent grant is currently assigned to Motoren-und Turbinen-Union GmbH. Invention is credited to Immanuel Holzapfel, Gerhard Zahring.
United States Patent |
3,894,324 |
Holzapfel , et al. |
July 15, 1975 |
Rotor for fluid flow machines
Abstract
A rotor arrangement and method of making the rotor arrangement
for fluid flow machines having a plurality of rotor disks, each
including a plurality of rotor blades, spaced from one another by
intermediate ring members. The intermediate ring members are
constructed as inner and outer rings with the inner ring welded to
the adjacent rotor disk and the outer ring detachably slidably
engaged over the inner ring by a dove-tail connection. The outer
surface of the outer rings form a continuous surface with rotor
blade platforms. Locking elements are connected at the platforms
and the disk to hold the blades and outer rings from axial
movement. With the slidable arrangement of the outer rings,
disassembly of the rotor blades, etc., is facilated. A modification
dispenses with the outer ring and includes labyrinth points on the
inner ring which sealingly cooperates with a ring member of stator
vane cascades interposed between the disks.
Inventors: |
Holzapfel; Immanuel (Stuttgart,
DT), Zahring; Gerhard (Munich, DT) |
Assignee: |
Motoren-und Turbinen-Union GmbH
(DT)
|
Family
ID: |
5816766 |
Appl.
No.: |
05/280,142 |
Filed: |
August 14, 1972 |
Foreign Application Priority Data
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Aug 14, 1971 [DT] |
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2140816 |
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Current U.S.
Class: |
29/889.2;
415/199.5; 416/201R; 416/198A |
Current CPC
Class: |
F01D
5/06 (20130101); Y10T 29/4932 (20150115) |
Current International
Class: |
F01D
5/02 (20060101); F01D 5/06 (20060101); B23p
015/00 () |
Field of
Search: |
;29/156.8R
;416/198R,198A,201,219 ;415/199R |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
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950,100 |
|
Oct 1956 |
|
DT |
|
586,041 |
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Mar 1946 |
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GB |
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574,752 |
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Jan 1946 |
|
GB |
|
Primary Examiner: Lanham; C. W.
Assistant Examiner: Crane; Dan C.
Attorney, Agent or Firm: Craig & Antonelli
Claims
What is claimed is:
1. A method of making a rotor arrangement comprising:
placing a plurality of rotor disks spaced from one another along a
common axis,
slidably inserting a plurality of rotor blades in slots provided at
the periphery of an endmost disk,
fixedly attaching an intermediate inner ring member to said endmost
disk and to the next adjacent disk, and
axially slidably positioning a continuous intermediate outer ring
member over the circumference of said inner ring member such that
the outer surface of said outer ring member forms a continuous
smooth surface with platform sections of said rotor blades,
wherein said outer ring member is a continuous closed ring, and
wherein said outer ring member and said inner ring member have
corresponding detachably slidable interengageable parts for
circumferentially and radially locking said outer and inner ring
members to one another, said step of axially slidably positioning
including interengaging said interengageable parts.
2. A method according to claim 1, wherein said plurality of rotor
disks includes at least three rotor disks, further comprising:
slidably inserting a plurality of rotor blades in slots provided at
the periphery of a second disk adjacent the endmost disk,
fixedly attaching a second intermediate inner ring member to said
second disk and to a third disk adjacent thereto at the side
opposite the endmost disk,
and axially slidably positioning a second intermediate outer ring
member constructed as a continuous closed ring over the
circumference of said second inner ring member such that the outer
surface of said second outer ring member forms a continuous smooth
surface with platform sections of said rotor blades.
3. A method according to claim 2, wherein said second outer ring
member and second inner ring member have corresponding detachably
slidable interengageable parts for circumferentially and radially
locking said second outer and second inner ring members to one
another, said step of axially slidably positioning including
interengaging said last mentioned interengageable parts.
4. A method according to claim 3, wherein the configuration of the
interengageable parts on each of the inner ring members is similar,
and wherein the step of axially slidably positioning said first
mentioned outer ring member includes sliding said first mentioned
outer ring member over said second inner ring member with the
interengageable parts of said second inner ring member permitting
free passage of said first mentioned outer ring member
thereover.
5. A method according to claim 4, wherein the respective
interengageable parts of said inner and outer ring members are
constructed as mating dovetail shaped teeth and slots.
6. A method according to claim 5, further comprising inserting
locking plates between a platform of the endmost disk and the
blades mounted thereon for preventing axial displacement of said
blades.
7. A method according to claim 6, further comprising inserting
locking plates between platforms of each of the other disks and
associated blades thereon for preventing axial displacement of said
last mentioned blades.
8. A method according to claim 2, wherein said steps of fixedly
attaching said inner ring members to said disks includes welding of
the respective inner ring members to respective ones of said
disks.
9. A method according to claim 32, wherein said steps of fixedly
attaching said inner ring members to said disks includes welding of
the respective inner ring members to respective ones of said
disks.
10. A method according to claim 29, wherein the dimensions of the
interengageable parts at said second inner ring member are such as
to permit a freer passage of said first mentioned outer ring member
thereover than the passage of said first mentioned outer ring
member over said first mentioned inner ring members.
11. A method of making a rotor arrangement comprising:
placing a plurality of rotor disks spaced from one another along a
common axis,
fixedly attaching inner intermediate ring members to said rotor
disks,
slidably inserting rotor blades in slots provided at the periphery
of an endmost rotor disk,
locking said rotor blades in said endmost disk,
slidably inserting a first intermediate outer ring member over the
outer circumference of said rotor disks and through slots provided
on said inner intermediate ring members to contact platforms
provided on said rotor blades,
slidably inserting rotor blades into slots of a second rotor disk
with its platforms contacting the face of said first intermediate
outer ring member, and
sequentially slidably inserting a plurality of further intermediate
outer ring members and rotor blades into slots in the remaining
rotor disks with the respective platforms of each rotor blade of a
respective rotor disk contacting the face of the preceeding
intermediate outer ring member such that the outer surface of said
intermediate outer ring member forms a continuous smooth surface
with the platform sections of said rotor blades.
Description
BACKGROUND AND SUMMARY OF THE INVENTION
The present invention relates to a rotor for fluid flow machines in
which a plurality of rotor disks are interconnected by means of
intermediate rings welded or otherwise fixed in place between
them.
Rotors in this category can normally not be disassembled, so that
it is very nearly impossible to replace damaged components in
especially the outer circumferential area of the rotor, such as the
rotor blades attached to the rotor or to the rotor disks.
Also, considerable difficulties are encountered in the designing of
such rotors when it is attempted to achieve an aerodynamically
favorable, that is, smoothly faired wall structure between the
blade platforms in rotors where it is desired to disconnectably
connect the rotor blades to the rotor disks and where intermediate
rings are welded in place in the outer circumferential area of the
rotor.
Under the same conditions rotor constructions like those discussed
above also cause notable difficulties when it is attempted to keep
dead weight comparatively low.
A broad object of the present invention is to eliminate the
disadvantages attributed to said rotors for fluid flow machines and
to provide a rotor which permits of relatively high operating
speeds and possesses the requisite strength to sustain such speeds
while overcoming the abovediscussed disadvantages and while having
a comparatively low dead weight.
To meet these and other objects the present invention contemplates
the provision of a rotor for fluid flow machines of the said
generic category in which the intermediate rings each include an
inner member which is welded in place and an outer member which is
slipped into place on the inner member. It is further contemplated
by the present invention that said outer member forms a smoothly
faired inner wall for the associated flow duct in conjunction with
the platforms on adjacent blades.
In rotors contemplated by the present invention the inner members
of the intermediate rings may be permanently connected to the disks
by electron beam or friction welding. The inner members of the
intermediate rings may further be composed of individual
segments.
The present invention contemplates the provision of the outer
member as a continuous closed ring and the provision of
corresponding detachably slidably interengageable parts for
circumferentially, and radially locking an inner and outer member
together. In a further aspect, the present invention contemplates
the provision of similar configurations for the interengageable
parts on a plurality of axially aligned inner members so as to
facilitate free passage of an outer member in the axial direction
of the rotor over and past several inner members to a position in
engagement with the corresponding mating inner member. Preferably
enough play is provided for permitting passage of the outer member
without leaving excess slack that cannot be taken up by elasticity
of the outer member when finally assembled and used.
In a preferred embodiment contemplated by this invention the outer
member of each intermediate ring forms a continuous ring having
radially disposed internal teeth for sliding it axially into mating
slots in the inner member of the intermediate ring, where the
respective shape and number, or pitch, of these slots are
essentially identical with the shape and pitch of the slots in the
remaining inner members but will still ensure free passage of the
outer member when this is being slipped into place. Alternatively,
the teeth could be provided on the inner member and the slots on
the outer members.
It is further contemplated by the present invention that the outer
member of each intermediate ring is prevented from excessively
expanding radially under service loads. A comparatively large
number of suitably selected dovetailed teeth and slots ensures a
maximally central position of the outer member of each intermediate
ring.
According to the invention, dovetail slots in the inner members of
the intermediate rings and in the outer members of the intermediate
rings may be produced by broaching much like the dovetail slots in
the blade shrouds of rotor disks. The dovetail slots in the inner
members of the intermediate rings may be broached before welding
exactly like those in the rotor disks.
The accuracy obtainable in shape and pitch of the dovetail slots in
the outer and inner member of each intermediate ring contemplated
by the present invention may be in the order of magnitude of that
of the dovetail slots in rotor disks. Inasmuch as the outer member
of each intermediate ring may be made elastic within reasonable
limits, minor deviations in the shape of the outer member of the
intermediate rings can be readily compensated during assembly.
Where a gentle incline exists of the inner contour of the blade
duct, the present invention contemplates that the dovetail contour
can be repeated unchanged on the same radius through several rotor
stages, so that a corresponding number of outer members of the
intermediate rings can be slipped with their teeth through the
slots in the inner members of the intermediate rings. For other
than dovetail connections, the present invention contemplates that
the interengageable parts of several rotor stages be similar for
inclined contour ducts.
In order to compensate for such minor inaccuracies in pitch as may
be caused in manufacture, a certain amount of clearance can be
provided between the teeth and the slots or other interengageable
parts. Their elasticity and expansion under centrifugal force will
nevertheless cause the outer members of the intermediate rings to
fit snugly as soon as a certain, still low speed is reached. The
resultant eccentricity of the outer members of the intermediate
rings can be held within allowable limits.
In a further aspect of the present invention the blades and with
them also the outer members of the intermediate rings may be
arrested in their axial position by means of locking elements.
A further modification contemplated by the present invention is the
arrangement of the inner members of the intermediate rings to be
reworked to provide, for instance, labyrinth points, and that
rotors intended for use in compressors may thus be retrofitted for
cooperation with internally shrouded vane cascades.
The present invention further contemplates the method of making the
rotor arrangements referred to above.
These and other objects, features and advantages of the present
invention will become more apparent from the following description
of several embodiments thereof, when taken in conjuction with the
accompanying drawings.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1 is a longitudinal center section view of a rotor in
accordance with the present invention which schematically
illustrates the step-by-step assembly of the rotor;
FIG. 2 is a schematic longitudinal center section view of the fully
assembled rotor of FIG. 1;
FIG. 3 is a partial schematic sectional view, with portions
cut-away, taken along line II--II of FIG. 2;
FIG. 4 is a detail schematic view illustrating the configuration
and attachment of the blade root to one of the rotor disks of FIGS.
1 and 2; and
FIG. 5 is a longitudinal center section schematic view illustrating
an alternative embodiment of the rotor shown in FIGS. 1 and 2.
DETAILED DESCRIPTION OF THE DRAWINGS
Reference is now made to the drawings wherein like reference
numerals refer to like structures throughout the various views.
With reference to FIG. 1, the numeral 2 indicates an axial-flow
compressor rotor which essentially comprises of the rotor disks 3,
4, 5, and 6. These rotor disks 3, 4, 5, and 6 are interconnected by
welding them in the areas of their shrouds 7, 8, 9, and 10 to the
inner members 11, 12, 13, of the intermediate rings 14, 15 and
16.
The welded axial-flow compressor rotor is fitted alternately and
viewed from left to right with the rotor blades 18, 19, 20, 21 and
the outer members 22, 23, 24, of the intermediate rings 14, 15, 16
(FIG. 1) preferably to suit the cross-sectional area of the
compressor air duct 17 (FIG. 2) which may be narrowing in the
direction of flow.
With reference to FIG. 1 the rotor blades 21, which have a
dovetailed root exemplified by the numeral 25 in FIG. 4, are
axially inserted in suitably shaped slots in the shroud 10 and
restrained from axial displacement by means of a locking plate 26
which is connected to the shroud 10. The outer member 24, which
forms a continuous ring, of the intermediate ring 16 is then
slipped over the mating inner member 13 until its face contacts
with the airfoil platform 27 of the blade 21. A dovetailed
connection 28 arrests the outer member 24 in its circumferential as
well as radial position on the inner member 13 of the intermediate
ring 16. The pitch and the contour of the teeth and of their mating
slots in the dovetail connection 28 are approximately identical
with those in the dovetail connections 29, 30 (FIG. 2) of the
intermediate rings 15, 14, so that the continuous-ring member 24
may readily be slipped with its teeth through the slots in the
inner members 11, 12 of the intermediate rings 14, 15 entering in
the dovetail connections 29, 30. The attachment or assembly of the
remaining outer members 22, 23 and blades 20, 19, 18 then proceeds
analogously, where the outer members 22, 23 of the intermediate
rings 15, 14 form, together with the platforms 31, 32, 33, of the
blades 18, 19, 20 a smoothly faired inner wall for the air duct 17
(FIG. 2).
FIG. 3 exemplifies a representative dovetailed connection 29
between the welded inner member 12 and the subsequently axially
seated outer member 23 of the intermediate ring 15.
FIG. 2 shows additional locking plates 34, 35, 36 which limit the
blade to disk connections at the forward end and are arranged
between the respective shrouds 7, 8, 9 (FIG. 1) and blade platforms
31, 32, 33.
FIG. 2 further illustrates the outer duct wall 27 of the compressor
air duct 17 which contains stator vanes 38, 39, 40.
It is also envisioned to slightly enhance the tooth clearance
increasingly from right to left (FIGS. 1 and 2) while retaining the
tooth pitch and slot contour of the dovetailed connections between
the inner and outer members of the intermediate ring so as to
ensure ease of positioning the outer members on the inner
members.
FIGS. 1 and 2 exemplify an axial-flow compressor rotor 2 where the
stator vane cascades are unshrouded at their inner diameter so that
when the rotor is turning, the fixedly arranged outer members 22,
23, 24 of the intermediate rings 14, 15, 16 are completely free to
move below the free ends of the stator vanes 38, 39, 40 without the
intervention of sealing devices.
FIG. 5 illustrates an axial-flow compressor rotor 41 which differs
from the embodiment on FIGS. 1 and 2 in that the inner member 12 of
the intermediate ring 15 which was formerly slotted to accommodate
the dovetailed connection 29 has now been shaped by reworking (42
in FIG. 5) to provide labyrinth points 43 which together with the
inner ring 45 attached to the stator vanes 44, form a
non-contacting or a contacting seal. In FIG. 5 the rotor disks are
indicated with the numerals 46, 47 and their rotor blades with 48,
49.
The invention described and shown in light of FIGS. 1 to 5 may
analogously be applied also to a turbine rotor.
Also, other embodiments reversing the teeth and slots on the inner
and outer members from the arrangements shown in FIGS. 1-4 are
contemplated by the present invention. Also, each of the inner and
outer members could include both teeth and slots engageable with
corresponding teeth and slots on the other member. Also, other
interengageable connections than dovetail connections could be
used.
While we have shown and described several embodiments in accordance
with the present invention, it is understood that the same is not
limited thereto but is susceptible of numerous changes and
modifications as will be apparent to a person skilled in the art,
and we therefore do not wish to be limited to the details shown and
described herein but intend to cover all such changes and
modifications.
* * * * *