U.S. patent number 3,733,146 [Application Number 05/131,973] was granted by the patent office on 1973-05-15 for gas seal rotatable support structure.
This patent grant is currently assigned to United Aircraft Corporation. Invention is credited to Stephen Lester Smith, Peter Edward Voyer.
United States Patent |
3,733,146 |
Smith , et al. |
May 15, 1973 |
GAS SEAL ROTATABLE SUPPORT STRUCTURE
Abstract
A toroidal structure which is lenticular in cross section and
rotatable in a gas turbine environment is disclosed. The structure
is described as a support member for the rotating component of a
seal assembly in a high temperature application, such as a turbine
rotor. The structure is radially supported by a pair of adjacent
turbine disks and comprises a pair of curved plates which cooperate
during rotation to cause a low net stress in the plates. The outer
plate has a raised ridge along each of its circumferential edges
and correspondingly the inner plate has a butt face along each of
its circumferential edges. During rotation of the lenticular
structure, the ridge edges tend to draw closer together and the
butt face edges tend to spread apart and since the inner plate
edges are restrained by the outer plate ridges, a transfer of axial
loads between the plates occurs, resulting in a reduction in the
net stress in the structure.
Inventors: |
Smith; Stephen Lester (South
Windsor, CT), Voyer; Peter Edward (Tolland, CT) |
Assignee: |
United Aircraft Corporation
(East Hartford, CT)
|
Family
ID: |
22451837 |
Appl.
No.: |
05/131,973 |
Filed: |
April 7, 1971 |
Current U.S.
Class: |
415/173.7;
415/199.5; 416/198A |
Current CPC
Class: |
F01D
5/06 (20130101); F01D 11/001 (20130101) |
Current International
Class: |
F01D
11/00 (20060101); F01D 5/06 (20060101); F01D
5/02 (20060101); F01d 011/08 (); F01d 001/04 () |
Field of
Search: |
;416/191,200,201,500
;415/191,192,193,194,199,115,171,172,117 ;60/39,66 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Raduazo; Henry F.
Claims
Having thus described typical embodiments of our invention, that
which we claim as new and desire to secure by Letters Patent of the
United States is:
1. In a gas turbine engine having an axial centerline, a rotatable
gas seal support structure having a toroidal shape which is
lenticular in cross section, the structure comprising:
a curved annular outer shell which is unpenetrated by bolt holes
and has a raised ridge along each of its circular end surfaces and
is symmetrically disposed about the axis so that during rotation of
the structure about the axis, the center of the outer shell tends
to move away from the axis and the distance of separation between
the two ridges along the axis tends to decrease; and
a curved annular inner shell which is unpenetrated by bolt holes
and has a butt face along each of its circular edge surfaces and is
positioned between the raised ridges of the outer shell so that
during rotation of the structure the center of the inner shell
tends to move away from the axis and the distance of separation
between the two butt faces along the axis tends to increase.
2. The invention according to claim 1 including means attached to
one of the adjacent turbine wheels for preventing relative
rotational motion between the turbine wheel and the double annular
shell.
3. The invention according to claim 1 wherein the curved outer
shell supports a knife edge member of a seal, the knife edge
cooperating with a land member of the seal which is attached to a
stationary member of the gas turbine.
4. In a gas turbine engine having a pair of adjacent, rotatable,
blade retaining, wheels with each wheel having an axially extending
and a radially extending containing surface symmetrically disposed
about the centerline axis of the engine, a rotatable gas seal
support structure having a toroidal shape which is lenticular in
cross section, the structure comprising an outer annular shell
which is curved concavely from the axial centerline and has two
circular end surfaces, and an inner annular shell which is curved
convexly from the axial centerline and has two circular edge
surfaces, the inner of said edge surfaces being held in axial
restraint by a corresponding outer end surfaces, the two annular
shells being axially and radially contained by the support surfaces
of the pair of wheels, the shells having no holes therethrough to
accommodate axial load bearing attachment means between the
structure and the wheels.
Description
BACKGROUND OF THE INVENTION
1. Field of the Invention
This invention relates to a curved rotatable structure having
internal circumferential stresses which are reduced by self-induced
loads, and more particularly, to a toroidal gas seal support
structure which is lenticular in cross section.
2. Description of the Prior Art
In a typical gas turbine arrangement, several turbine wheels each
comprising a row of blades on the periphery of a disk make up a
rotor which is enclosed within an engine stator. The working medium
passes across the turbine blades and gas leakage around the ends of
the blades is minimized by a seal arrangement at the tips of the
blades. On opposite sides of the rows of blades are rows of stator
vanes which direct the flow of the working medium. The stator vanes
are rigidly attached to the engine case and project inward toward
the engine rotor. Leakage of the working medium around the inner
ends of the stator vanes of each row is minimized with a seal
arrangement analogous to that provided at the tip of the turbine
blades; the rotating member of the seal is supported by structure
which is essentially a cylinder extending between adjacent disks
and rotating therewith. The seal is located immediately adjacent to
the inner ends of the stator vanes. This type of gas seal between
the various pressure stages in turbines has been used repeatedly
and effectively.
Relatively large diameter gas turbine engines which operate at
conditions of greatly increased temperatures and rotational speeds
are presently being developed. As operating conditions such as
rotational speed and turbine temperature become more demanding,
design limitations which were not prevalent in the small diameter
engines are becoming apparent. For example, the stress experienced
by a rotating cylinder is proportional to the distance the cylinder
is from the center of rotation and rotational speed. For a given
material at a given operating temperature and speed of rotation,
there is a maximum radius from the center of rotation beyond which
the component may not be located without exceeding the acceptable
stress limit for that component; this radius is sometimes referred
to as the self-sustaining radius.
The operating parameters of some engines are such that the rotating
portion of a seal in some stator sections of the engine exceeds the
self-sustaining radius, a condition which is intolerable since it
can lead to structural failures. To avoid the problem, a platform
structure may be added at the tips of the stators so that the seal
is located closer to the engine centerline, with the rotating
portion of the seal within the self-sustaining radius
limitation.
The platform extension avoids the above-mentioned structural
shortcoming, however, a different problem is introduced. There is a
pressure differential across the stator in the direction of gas
flow; also, the stator is supported at its outer end (at the point
of maximum stator radius) by the engine casing so that the stator
is essentially a cantilevered structure. The pressure differential
across the platform section causes the stator to bend in the
direction of lower pressure more than would otherwise occur. In
some cases, the combination of distance between the seal and the
support provided the stator at the casing, and the pressure drop
across the seal is sufficient to cause the stator to bend and
interfere with the next stage of the turbine rotor, thereby causing
grinding of the rotor by the stator extension in the area of the
seal.
SUMMARY OF THE INVENTION
An object of the present invention is to provide a gas seal for a
relatively large diameter, high temperature gas turbine
application.
According to the present invention, an annular rotatable structure,
lenticular in cross section and formed into a toroid about a
central axis of rotation is radially supported by a pair of rotors
in a gas turbine; the structure comprises a curved annular outer
shell having circular edge surfaces whose distance of separation
along the axis of rotation tends to be reduced during rotation, and
a curved annular inner shell also having circular edge surfaces
which mate with the edge surfaces of the outer shell and which tend
to separate along the axis during rotation; the spreading axial
tendency of the inner shell counteracts the contracting axial
tendency of the outer shell resulting in net reduced stress in the
toroidal structure during rotation.
An advantage of the present invention is the elimination of
connecting bolts between the rotating seal structure and the
adjacent gas turbine rotors. In addition, the bolting of the disks
to the seal support develops internal axial loading and bending in
the disks.
A further advantage of this invention is the ability to provide a
rotating support member for a seal in a gas turbine at a distance
from the center of rotation which would otherwise be beyond the
self-sustaining radius. Also, since the structure is supported
radially by the turbine disks, the structure has a radial growth
during acceleration which is matched to that of the disks.
The present invention also minimizes the overturning moment
experienced by a stator vane since the distance between the sealing
surface and the point at which the stator is rigidly held at one
end by the engine case is reduced.
One feature of the present invention is the thermal fitting of the
inner and outer shells; sufficient heating and cooling of the outer
and inner shells respectively are required to allow the inner shell
to be positioned internal of the outer shell and then to expand to
fit securely between the retaining ridges as both shells approach
an equilibrium temperature.
An additional feature of this invention is that the lenticular
structure tends to stiffen the gas turbine rotors between which
such an assembly is located. Further, this invention affords a
greater safety margin since the seal support structure (the
lenticular member) operates with a net stress which is lower than
would otherwise be possible.
The foregoing and other objects, features and advantages of the
present invention will become more apparent in the light of the
following detailed description of a preferred embodiment thereof as
illustrated in the accompanying drawing.
BRIEF DESCRIPTION OF THE DRAWING
The sole FIGURE herein is a simplified schematic drawing of a seal
in accordance with the present invention.
DESCRIPTION OF THE PREFERRED EMBODIMENT
A preferred embodiment of the present invention takes the form of a
rotating shell structure which is located between adjacent disks of
the high pressure turbine in a large diameter gas turbine engine.
As shown in the drawing, each of a pair of turbine disks 10 and 12
supports on its periphery a turbine blade 14 and 16, respectively.
A stator vane 18 extends inwardly from an engine case (not shown)
and is connected by means of bolts 20 to a stationary ring 22 of a
segmented seal assembly 24 having a series of lands 26. Each of the
turbine blades 14 and 16 as well as the stator vane 18 are but one
of a circular row of respectively similar items. Blocking plates 28
and 30 are also attached by the bolts 20 to the opposite sides of
the ring 22 to prevent gas leakage between adjacent seal
segments.
The seal structure mounted between the turbine disks includes an
inner curved shell 32 having a meridian 34 and outer curved shell
36 having a meridian 38 which together form a double annular
structure 40 having a lenticular shaped cross section. A series of
knife edges 42 which mate with the lands 26 to form the seal
assembly 24 is supported by the outer shell 36. Side plates 48 and
50 form part of the structural assembly and are mounted on the
adjacent faces of the turbine disks. An antirotation lug 52
projects from the turbine disk 10 and cooperates with an extension
member 54 of the outer shell 36 thereby preventing any relative
rotary motion between the double annular structure 40 and the
turbine disks.
The magnitude of the circumferential stress in the outer shell 36
allows the stator vanes to be sealed at a much larger radius than
was previously possible due to the presence of the curved inner
shell 32; both these shells are designed so that when the structure
is rotated, meridional tensile [normal to the circumferential
stress] is produced in the outer shell and meridional compressive
load is produced in the inner shell because the two shells interact
with each other such that the axial loads (parallel to engine
centerline) imposed by one shell on the other tend to cancel one
another. The net circumferential stress experienced by each of the
shell members is reduced by a negative circumferential stress
produced by the induced axial load in each shell.
The double annular structure 40 is supported radially by the
turbine disks 10 and 12 by pilots 44 and 46, respectively. During
rotation of the structure 40, the central region of the outer shell
36 tends to grow radially in the direction of the stator vanes due
to the rotary motion and the edge ridges 56 and 58 tend to move
axially toward each other. Simultaneously, the center region of the
inner shell also tends to move in the direction of the stator
vanes, in much the same manner as the outer shell 36 reacted to
rotation, with the edges or butt faces 60 and 62 of the inner shell
32 tending to spread or move away from one another in the axial
direction. As the edge ridges 56 and 58 move toward one another,
the inner shell 32 is subjected to a compressive axial load which
is counteracted in the outer shell by the tensile axial load
resulting from the axial spreading of the butt faces 60 and 62 of
shell 32.
The operating tensile circumferential stress is thereby reduced by
a negative circumferential stress produced by the induced axial
load in each shell. Additional circumferential stress reduction is
produced by radial restraint on the ends of structure 40 at pilots
44 and 46.
The overall result is both the inner and outer shells of the double
annular structure 40 have relatively low net internal
circumferential stresses; the axial loads in each shell, due to the
restraints each shell puts on movement of the ends of the other
shell, yields a circumferential stress which is less than that
which a cylindrical structure would experience at the same radius,
speed and temperature.
When it became evident that right cylindrical shells and the
platform extension structure previously mentioned were not
satisfactory in highly stressed seal support applications, a curved
shell which could be bolted to the adjacent turbine disks was
considered. While a rotating support structure consisting of a
single sleeve is conceptually feasible, this approach is
undesirable because the bolt holes in the turbine disks near the
rim have been found to reduce low cycle fatigue life resulting in
increased disk weight to regain the lost low cycle fatigue life. In
additional, the bolting of the disks to the seal support develops
internal axial loading and bending in the disks. By way of
contrast, the double annular rotating seal support structure in
accordance with this invention does not require holes in the
adjacent turbine disks for attachment purposes.
The axial support for a single curved shell bolted to the adjacent
disks is provided by both the axial stiffness of the disks and the
spacer between disks. Since the disks are generally circular plates
which are inefficient axial load carrying members, less axial
meridional load can be maintained in a bolted single shell than in
an unbolted lenticular shell, and under the same operating
conditions, the single shell experiences greater circumferential
stress.
Since the stationary segmented portion of the seal has a controlled
response to thermal cycle changes, the overall characteristic of
the seal is controlled seal clearances during acceleration of an
engine followed by a period when the seal clearances slowly
approach the steady state clearance and a fairly constant clearance
of the sealing members during deceleration with no rubbing of
mating seal surfaces due to differences in thermal growth at any
time in the cycle.
Since both the inner shell and the outer shell are one piece
annular members, their assembly into a double annular structure is
done in the following manner. The inner or smaller diameter shell
is cooled and the outer or larger diameter shell is heated until
the outside diameter of the butt face 62 of the inner shell is less
than the inside diameter of the end ridge 58 of the outer shell. By
way of example, if the shells are stainless steel having a diameter
of approximately 30 inches, and the end ridge height is
approximately 100 mils, a temperature difference between the inner
and outer shell of approximately 1,000.degree. has been found
sufficient to allow the described joining to be accomplished.
Although the invention has been described with respect to preferred
embodiments thereof, it should be understood to those skilled in
the art that the foregoing and other changes in the form and detail
thereof can be made therein without departing from the spirit and
the scope of the invention.
* * * * *