U.S. patent number 3,861,827 [Application Number 05/450,542] was granted by the patent office on 1975-01-21 for diaphragm support lugs.
This patent grant is currently assigned to General Electric Company. Invention is credited to Robert F. Cericola, Bayard W. Peabody.
United States Patent |
3,861,827 |
Peabody , et al. |
January 21, 1975 |
DIAPHRAGM SUPPORT LUGS
Abstract
In a turbomachine casing divided along a horizontal joint into
upper and lower casing halves, a diaphragm is supported on each
side by upper and lower lugs including shoulder portions which
interlock with respective upper and lower diaphragm halves. A
vertical pin is inserted through each shoulder and into abutting
diaphragm portions to prevent relative movement between the turbine
casing and diaphragm.
Inventors: |
Peabody; Bayard W.
(Baldwinville, ME), Cericola; Robert F. (Greenville,
SC) |
Assignee: |
General Electric Company
(Schenectady, NY)
|
Family
ID: |
23788498 |
Appl.
No.: |
05/450,542 |
Filed: |
March 12, 1974 |
Current U.S.
Class: |
415/209.2;
415/199.5 |
Current CPC
Class: |
F01D
25/246 (20130101) |
Current International
Class: |
F01D
25/24 (20060101); F01d 025/24 (); F01d
025/28 () |
Field of
Search: |
;415/126,219R,217,218,199 ;248/2,14,17 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Croyle; Carlton R.
Assistant Examiner: Casaregola; L. J.
Attorney, Agent or Firm: Ahern; John F. Mitchell; James
W.
Claims
What is claimed is:
1. A turbomachine including an outer casing divided along a
horizontal joint into upper and lower outer casing halves and
further including a diaphragm within the outer casing, the
diaphragm divided into upper and lower diaphragm halves within the
outer casing; and, means for mounting the diaphragm halves within
their respective outer casing halves comprising:
upper and lower casing lugs mounted in a cutout portion on each
side of the outer casing;
a shoulder formed on each lug;
a slot formed on each side of a respective diaphragm half, each
shoulder extending into its respective diaphragm slot;
at least one substantially vertical fastener on each side of the
turbomachine casing, each fastener having a portion thereof
positioned in at least one shoulder and another portion thereof
positioned in the diaphragm whereby movement of the diaphragm
relative to the outer casing is prevented.
2. The device recited in claim 1 wherein there is one substantially
vertical fastener for each casing lug, the fastener inserted
through each shoulder and having each end terminating in a portion
of the diaphragm abutting the shoulder.
3. The device recited in claim 1 wherein each vertical fastener is
a smooth pin.
4. The device recited in claim 1 wherein each lug shoulder and each
diaphragm slot extend in the axial direction.
5. The device recited in claim 1 wherein each vertical fastener is
perpendicular to the horizontal centerline of the turbomachine.
Description
BACKGROUND OF THE INVENTION
This invention was made under contract with the U.S. Government,
Department of the Navy. The invention relates, in general, to
turbomachines; and, in particular, to means for supporting a
turbine diaphragm relative to the turbine outer casing.
A turbomachine such as a steam turbine includes an outer casing
having a rotor mounted therein. An axial flow steam path may be
defined by several stages each comprised of a turbine wheel and a
diaphragm. Each turbine wheel is attached to the rotor, rotatable
therewith, and includes an annular array of radial, outwardly
extending blades. Each diaphragm is attached to the turbine outer
casing and forms an annulus around the rotor. The diaphragm
includes stationary nozzles approximately aligned with its
respective turbine wheel blades and at its inner diameter includes
shaft packings. As is well known in the art, the purpose of the
diaphragm is to prevent axial leakage of steam while defining an
axial flow path for steam through its nozzle portion. Accordingly,
radial clearances between the diaphragm and outer casing; and,
between the diaphragm and rotor are critical. Misalignment, caused
by support lug failure may have deleterious effects on turbine
operation such as loss of efficiency and packing rub which can
necessitate turbine shutdown.
It is one object of the present invention to provide a diaphragm
support capable of withstanding vertical shock loads.
It is another object of the present invention to provide a
diaphragm support wherein staking screws are obviated.
The present invention is applicable but not limited to
turbomachines used in naval applications such as submarines. Such
vessels may encounter vertical shock loadings due to enemy ordnance
such as depth charges. This invention is particularly useful in
turbomachinery having an outer casing divided along its horizontal
centerline into upper and lower casing halves. Each casing half on
each side includes a step or cutout for accommodating upper and
lower support lugs. Each support lug is formed with an axially
extending shoulder which is inserted into a respective upper or
lower diaphragm slot forming an interlocking joint on each side of
the turbine casing upper and lower halves. Vertical dowels or pins
are inserted through each lug shoulder and abutting diaphragm
portions whereby relative movement is prevented between the turbine
casing and diaphragm.
The novel features believed characteristic of the present invention
are set forth in the appended claims. The invention itself,
however, together with further objects and advantages thereof, may
best be understood with reference to the following description,
taken in connection with the appended drawing.
BRIEF DESCRIPTION OF THE DRAWING
FIG. 1 is an end elevation view of a turbomachine casing and
diaphragm.
FIG. 2 is an enlarged side elevation view of a turbomachine
horizontal joint in the axial direction according to the prior
art.
FIG. 3 is an enlarged side elevation view of a turbomachine
horizontal joint in the axial direction according to the present
invention.
DETAILED DESCRIPTION OF THE INVENTION
Referring now to FIG. 1, a turbomachine outer casing 11, divided
along its horizontal joint, includes upper and lower casing halves
11A and 11B, respectively. Within the outer casing is a diaphragm
13, also divided along its horizontal axis into upper and lower
diaphragm halves 13A and 13B. When assembled, the diaphragm forms
an annulus about the rotor (not shown) including an annulus of
nozzle blades 15. Part of the diaphragm support is provided by lugs
17 on each side of the outer casing. There may be other support
means provided between the diaphragm and outer casing such as a
vertical adjustment screw (not shown) along the vertical axis in
the lower casing but this does not form part of the present
invention.
FIG. 2 shows one type of diaphragm support according to the prior
art wherein like numbers correspond to like parts. Upper and lower
casing halves include a step or cutout portion 19 along the
horizontal axis at the diaphragm location. Lower lug 17B includes a
shoulder 21B which extends axially into slot 23B formed in the
lower diaphragm. A screw 25B is then inserted parallel to the
horizontal joint through lug 17B and into the lower diaphragm 13B.
The screw 25B is then staked by a vertical pin 27. Alignment of the
diaphragm may be provided by shaving the underside of lower lug
17B.
The upper diaphragm 13A is assembled to the upper outer casing 11A
in a similar manner. Upper lug 17A is inserted into cutout 19 and
includes an axially extended shoulder 21A. The shoulder 21A is
inserted into a slot 23A in the diaphragm and the assembly is held
together by screw 25A. Screw 25A is staked by the bolt 29 which is
drilled into the upper casing half. Bolt 29 is a lifting bolt so
that when upper casing 11A is removed from the lower casing, the
diaphragm will be retained in the upper casing.
Having described the prior art, and now referring to FIG. 3 wherein
like parts are given like numbers, upper and lower casing halves
11A and 11B have a stepped or cutout portion 19 at the diaphragm
location, one on each side of the turbine for each diaphragm. A
lower lug 17B is axially inserted into the cutout and includes a
shoulder 21B inserted into a diaphragm slot 23B of the lower
diaphragm half 13B. An upper lug 17A is inserted into the cutout
and includes a shoulder 21A inserted into a diaphragm slot 23A of
the upper diaphragm half 13A. A lifting bolt 29 anchors the upper
diaphragm to the upper casing.
Both the upper and lower lug shoulders 21A and 21B are formed with
holes 31A and 31B, respectively, which are in the vertical
direction. Each diaphragm half is formed with upper holes 33A and
lower holes 33B which are vertical and aligned with the shoulder
holes. An upper vertical fastener 35A and a lower vertical fastener
35B are inserted in the upper and lower shoulder and diaphragm
holes. The vertical fasteners may be dowel pins.
The following advantages and operations are now pointed out with
respect to FIG. 3. Staking pins in the lower support lugs are
obviated. Vertical pins 35A and 35B are dowel pins and hence not
threaded providing a stronger connection between the lug shoulders
and diaphragms. Under vertical shock loading slight deformations of
the shoulders, in the arrangement shown in FIG. 2 (prior art) may
cause failure in tension and bending of screws 25A and 25B whereas
vertical loadings in the invention as shown and described in FIG. 3
can withstand considerably higher vertical shock loadings.
While there is shown what is considered, at present, to be the
preferred embodiment of the invention, it is, of course, understood
that various other modifications may be made therein. Such
modifications may include a single dowel pin rather than upper and
lower dowel pins for each side of the turbine casing. It is
intended to claim all such modifications as fall within the true
spirit and scope of the present invention.
* * * * *