U.S. patent application number 11/566044 was filed with the patent office on 2008-06-12 for spherical flange assembly.
This patent application is currently assigned to Pratt & Whitney Rocketdyne, Inc.. Invention is credited to Maynard L. Stangeland, Ronald Urquidi.
Application Number | 20080136183 11/566044 |
Document ID | / |
Family ID | 35238780 |
Filed Date | 2008-06-12 |
United States Patent
Application |
20080136183 |
Kind Code |
A1 |
Stangeland; Maynard L. ; et
al. |
June 12, 2008 |
SPHERICAL FLANGE ASSEMBLY
Abstract
A spherical flange assembly is disclosed. The spherical flange
assembly comprises a seat member, a heel member, a seal gland and
at least one nut and bold assembly. The seat member includes a
concave portion. The heel member includes a convex portion and a
seal gland opening. The seal gland is disposed within the seal
gland opening.
Inventors: |
Stangeland; Maynard L.;
(Thousand Oaks, CA) ; Urquidi; Ronald; (Van Nuys,
CA) |
Correspondence
Address: |
THOMAS, KAYDEN, HORSTEMEYER & RISLEY, LLP
600 GALLERIA PARKWAY, S.E., STE 1500
ATLANTA
GA
30339-5994
US
|
Assignee: |
Pratt & Whitney Rocketdyne,
Inc.
Canoga Park
CA
|
Family ID: |
35238780 |
Appl. No.: |
11/566044 |
Filed: |
December 1, 2006 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
|
|
10838282 |
May 4, 2004 |
7144049 |
|
|
11566044 |
|
|
|
|
Current U.S.
Class: |
285/412 |
Current CPC
Class: |
F16L 27/1012
20130101 |
Class at
Publication: |
285/412 |
International
Class: |
F16L 23/00 20060101
F16L023/00 |
Claims
1.-23. (canceled)
24. A spherical flange assembly for an engine, comprising: a seat
member having a concave portion; a heel member having a convex
portion in mated association with the concave portion, wherein the
heel member is rigidly and removably connected to the seat member
along approximately 45 degree nested interface formed by the
concave portion and the convex portion; and a seal disposed in a
three-sided seal groove, wherein the three-sided seal groove is
formed in the heel member along the convex portion; wherein the
concave portion begins at the internal radius of a first duct and
wherein the convex portion begins at the internal radius of a
second duct, wherein the first duct is integrally formed as part of
the seat member and the second duct is integrally formed as part of
the heel member.
25. The spherical flange assembly of claim 24, wherein the seat
member further comprises a first flange having a plurality of first
apertures and wherein the heel member further comprises a second
flange having a plurality of apertures, wherein the plurality of
first apertures and the plurality of second apertures are
configured to receive a plurality of fasteners for rigidly and
removably connecting the heel member to the seat member along the
approximately 45 degree nested interface.
26. The spherical flange assembly of claim 24, wherein the convex
portion of the heel member comprises a spherical radius of
approximately 1.5 to 2.5 times the internal radius of the second
duct and wherein the concave portion of the seat member comprises a
spherical radius substantially equal to the spherical radius of the
convex portion.
27. The spherical flange assembly of claim 24, wherein fluid or gas
inside the first and second ducts during operation of the engine
improves the effectiveness of the seal to insure essentially zero
leakage past the seal.
28. The spherical flange assembly of claim 24, wherein the
spherical flange assembly is configured to convey a fluid
comprising a pressure of up to 8000 psi and a temperature as low as
minus 400.degree. F. during operation of the engine without leakage
of the fluid past the seal.
29. The spherical flange assembly of claim 24, wherein the
spherical flange assembly is configured to convey a gas comprising
a pressure of up to 6000 psi and a temperature of up to
1200.degree. F. during operation of the engine without leakage of
the gas past the seal.
30. The spherical flange assembly of claim 24, wherein an amount of
angular misalignment is permitted between the seat member and the
heel member, the amount of angular misalignment comprising no more
than one-half the difference between a first angle defined by a
central angle of the concave portion and a second angle defined by
a central angle of the three-sided seal groove opening, wherein the
first angle and the second angle have a common vertex.
31. A spherical flange assembly, comprising: a seat member
comprising a concave portion defining a first arc length; a heel
member comprising a convex portion defining a second arc length,
wherein the heel member is rigidly and removably connected to the
seat member along an approximately 45 degree nested interface
formed by the concave portion and the convex portion, wherein the
second arc length nests entirely within the first arc length when
the spherical flange assembly is nominally aligned; and a seal
disposed along with approximately 45 degree nested interface in an
annular seal groove comprising two opposing side walls and a
bottom.
32. The spherical flange assembly of claim 31, wherein the seal
groove is disposed approximately midway along the convex
portion.
33. The spherical flange assembly of claim 31, wherein the seal
groove is formed in the heel portion approximately midway along the
convex portion.
34. The spherical flange assembly of claim 31, wherein an amount of
angular misalignment is permitted between the seat member and the
heel member, the amount of angular misalignment comprising no more
that one-half the difference between a first angle defined by a
central angle of the first arc length and a second angle defined by
a central angle of the seal groove opening, wherein the first angle
and the second angle have a common vertex.
35. A spherical flange assembly, comprising: a seat member
comprising a concave portion defining a first arc length; a first
flange having a plurality of first apertures; and a first duct,
wherein the concave portion, the first flange, and the first duct
are integrally formed as part of the seat member; and a heel member
comprising a convex portion defining a second arc length; a second
flange having a plurality of second apertures; and a second duct,
wherein the convex portion, the second flange, and the second duct
are integrally formed as part of the heel member, wherein the heel
member is rigidly and removably connected to the seat member along
an approximately 45 degree nested interface formed by the concave
portion and the convex portion, wherein the second arc length nests
entirely within the first arc length when the spherical flange
assembly is nominally aligned, wherein the plurality of first
apertures and the plurality of second apertures are configured to
receive a plurality of fasteners for rigidly and removably
connecting the heel member to the seat member along the
approximately 45 degree nested interface, and wherein each of the
plurality of fasteners comprise a nut, a bolt, a nut spherical
washer, and a bolt spherical washer.
36. A spherical flange assembly, comprising: a seat member,
comprising a concave portion; a first flange having a plurality of
first apertures; and a first duct, wherein the concave portion, the
first flange, and the first duct are integrally formed as part of
the seat member; a heel member, comprising a convex portion; a
second flange having a plurality of second apertures; a second
duct; and a seal groove disposed along the convex portion for
receiving a seal, wherein the convex portion, the second flange,
and the second duct are integrally formed as part of the heel
member, wherein the seal groove is annular and comprises two
opposing side walls and a bottom, and wherein the heel member is
rigidly and removably connected to the seat member along
approximately 45 degree nested interface formed by the concave
portion and the convex portion.
37. A spherical flange assembly, comprising: a seat member,
comprising a concave portion; a first flange having a plurality of
first apertures; and a first duct, wherein the concave portion, the
first flange, and the first duct are integrally formed as part of
the seat member; a heel member, comprising a convex portion; a
second portion; a second flange having a plurality of second
apertures; a second duct; and a seal groove disposed approximately
midway along the convex portion for receiving a seal, wherein the
convex portion, the second flange, and the second duct are
integrally formed as part of the heel member; and wherein the heel
member is rigidly and removably connected to the seat member along
an approximately 45 degree nested interface formed by the concave
portion and the concave portion.
Description
CROSS-REFERENCE
[0001] This invention is a continuation of U.S. patent application
Ser. No. 10/838,282 filed on May 4, 2004, which is incorporated
herein in its entirety.
FIELD OF THE INVENTION
[0002] The present invention is directed to spherical flange
assemblies and, in particular, to spherical flange assemblies that
allow for angular misalignment without resulting in either large
duct loads or joint leakage.
BACKGROUND OF THE INVENTION
[0003] Currently, aircraft designers and manufacturers use various
flexible, joints throughout the manufacture of the jet engines for
use in the aircraft. To this end, various attempts to develop a
satisfactory flexible, moderately pressurized joint have been
made.
[0004] For example, U.S. Pat. No. 4,448,449, issued to Halling, et
al. and entitled "Flexible Piping Joint and Method of Forming Same"
(Halling), discloses a fluid-tight coupling and sealing apparatus.
Hailing describes a flexible piping joint, for use in fluid systems
at moderate pressures and temperatures, that require a limited
amount of angulation during operation. The invention in Halling,
however, employs structurally inefficient load paths and
non-metallic sealing elements. Further, these elements are not
feasible at the extreme temperatures and pressures of rocket engine
applications. Moreover, the sealing interface depends on the
interference fit between the non-metallic seal and the metal duct
material, both of which have significantly different thermal
coefficients of expansion which limit the allowable operating
temperature range. Additionally, the spherical interface must react
with the pressure-separating load with the hoop strength of the
concentric rings through a very structurally inefficient contact
angle. Thus, for high pressure applications, the ring thicknesses
would be significant, resulting in a very heavy structure, much
larger in diameter for a given duct diameter.
[0005] U.S. Pat. No. 4,772,033, issued to Nash and entitled
"Flexible Duct Joint Utilizing Lip in Recess in a Flange" (Nash),
discloses a flexural joint for connecting opposing ends of two
annular ducts. The invention in Nash is directed towards large
diameter thin wall jet engine casing joints that permit both
torsional and transverse motion. The spherical interface possesses
a much larger diameter than the casing diameter, with the retaining
bolt pattern possessing an even larger diameter. However, this type
of structurally inefficient interface is also only acceptable for
low-pressure applications that do not have to react large
separating loads. For example, in high-pressure applications, the
interface seal must be positioned close to the duct internal
diameter to minimize the pressure separating load. Additionally,
the interface bolts must be preloaded at a stiffness level
sufficient to preclude separation at the seal interface with the
high operating pressures. Thus, the teachings of Nash are not
applicable or structurally feasible for high-pressure
applications.
[0006] Finally, U.S. Pat. No. 5,697,651, issued to Fernandes and
entitled "Flexible Duct Joint Having a Low Leakage,
Pressure-Balanced Bellows Seal" (Fernandes), discloses a flexible
joint for sealing two conduits. Fernandes discloses a flexible duct
joint for aircraft engines possessing compressed air ducting joints
that operate at relatively low pressures, as compared to rocket
engine joints. The joint concept permits angulation motion during
operation with limited leakage which is acceptable in the
compressed air system. However, Fernandes utilizes joint structural
shapes, retention mechanisms and multi-convolution bellows that are
not feasible for rocket engine high pressure cryogenic and hot gas
systems that require zero leakage.
[0007] Although the aforementioned references do provide flexible
joints to overcome jet engine operating conditions, the references
nevertheless fail, in one form or another, to facilitate the much
more extreme conditions that exist in a rocket engine. This is
primarily due to the fact that the aforementioned references are
typically conceived for applications with operating pressures less
than 1000 pounds per square inch (psi). The references are,
generally speaking, not structurally efficient or feasible enough
for applications within the 8000 psi range.
[0008] Since the early development of liquid-fuel rocket engines,
the need to transfer propellants from low pressure supply tanks to
turbopumps, turbine-driven pumps that raise the propellants used
therein to pressures high enough for injection into a combustion
chamber, has required specialized ducting that can, inter alia,
accommodate assembly misalignments, thermal induced defections and
both pressure- and vibration-induced loads. Early rocket engines
typically operated at combustion chamber pressures of less than
1,000 pounds per square inch (psi), which required pump discharge
pressures of less than 2,000 psi. For these applications, ducting,
including tied bellows and braided hoses adapted from the aircraft
engine and petro-chemical industries, were utilized to accommodate
the aforementioned misalignment and deflections.
[0009] However, as combustion chamber pressures were increased from
less than 1,000 psi to greater than 3,000 psi and closed cycle
engines were introduced, a need for propellant ducts operating at
up to 8,000 psi at temperatures as low as -400.degree. F. and hot
gas ducts operating at up to 6,000 psi at temperatures as high as
1,200.degree. F. were established. The use of tied bellows or
braided hoses are not feasible at these operating conditions, so
solid wall ducts possessing sufficient length and routing, and
flexible enough to accommodate the deflections were utilized. The
excessive weight of the complex ducting created the need for flange
joints that could accommodate assembly misalignments and react to
the pressure- and vibration-induced loads without leakage at the
extreme operating conditions.
SUMMARY OF THE INVENTION
[0010] The present invention discloses a spherical flange assembly
for overcoming the above-stated disadvantages, while also
accommodating the preferred operating conditions listed herein. A
spherical flange interface, such as that disclosed below,
preferably allows for a significant amount of angular misalignment.
Incorporating the spherical flange apparatus at both ends of a duct
accommodates both angular and offset misalignment. This results in
an easier assembly of engine components and lower resultant loads
which, in turn, makes for a more reliable joint due to better
sealing conditions at the spherical flange interface. Additionally,
the spherical flange of the present invention accommodates the
misalignment of high pressure ducts, thereby reducing misalignment
loads, decreasing engine weight and facilitating assembly.
[0011] Misalignment of adjacent surfaces is allowed by providing a
shape that permits joining the adjacent surfaces. More
specifically, a spherical, convex surface is machined in the heel
portion of one flange, protruding from the structural surface. Into
this heel portion, a seal groove is machined that will receive a
seal, either a packing or a pressure-assisted seal. The
pressure-assisted seal can have an uneven leg shape that can pick
up the spherical surface shape, or it can be made of differing
glands. A matching spherical, concave surface is machined into the
mating interface flange, also known as the seat portion. Sufficient
clearance is left between the flange portions when the spherical
interfaces are engaged to allow them to rotate for the
predetermined angular misalignment. Bolts are then set in holes
corresponding to the size of the clearance between the flange
portions, with spherical washer sets under the bolt head and nut,
thus providing bolt alignment consistent with the flange motion.
The bolts are disposed on the apparatus in a uniform manner. This
process precludes separation at the seat-to-heel interface when
pressure and other operating loads are applied.
[0012] To this end, a spherical flange assembly is disclosed. The
spherical flange assembly comprises a seat member, a heel member, a
seal gland and at least one nut and bolt assembly. The seat member
includes a concave portion. The heel member includes a convex
portion and a seal gland opening. The seal gland is disposed within
the seal gland opening.
[0013] A better understanding of the objects, advantages, features,
properties and relationships of the present invention will be
obtained from the following detailed description and accompanying
drawings, which set forth an illustrative embodiment and which are
indicative of the various ways in which the principles of the
present invention may be employed.
BRIEF DESCRIPTION OF THE DRAWINGS
[0014] For a better understanding of the invention, reference may
be had to various embodiments, as shown in the following drawings,
in which:
[0015] FIG. 1 illustrates a cross-sectional view of a spherical
flange interface assembly, manufactured in accordance with the
present invention;
[0016] FIG. 2 illustrates a cross-sectional view of the spherical
flange interface assembly of FIG. 1;
[0017] FIG. 3 illustrates a cross-sectional view of the seat member
of the spherical flange assembly of FIG. 1;
[0018] FIG. 4 illustrates a cross-sectional view of the heel member
of the spherical flange assembly of FIG. 1; and
[0019] FIG. 5 illustrates an embodiment of the spherical flange
interface assembly of FIG. 1, manufactured in accordance with the
present invention and misaligned 2 degrees.
DETAILED DESCRIPTION OF THE PRESENTLY-PREFERRED EMBODIMENTS
[0020] Due to the inherent tolerance variability of hardware,
flange misalignments can occur during the installation of mating
components for a liquid-propellant rocket engine. Further, these
flange misalignments can include axial, lateral and/or angular
offsets. If these misalignments are high, they can import
significant loads into the two mating components, which can lead to
failure. To address this flange misalignment issue, a spherical
flange assembly was developed that allows for misalignment yet
reduces imparted loads, while at the same time provides sufficient
sealing against leakage. The design of the present invention was
tested to evaluate and compare performance parameters, such as, for
example, misalignment and leakage. During the testing, the
environmental conditions ranged from -100 to +400 degrees
Fahrenheit (.degree. F.), with 1000 to 6000 pounds per square inch
(psi) pressure being applied to the spherical flange assembly.
[0021] Referring to the Figures, and in particular FIG. 1, which
illustrates one embodiment of the present invention, spherical
flange assembly 10 is illustrated in cross-sectional form. As
illustrated in FIG. 1, spherical flange assembly 10 comprises,
generally, seat member 12, heel member 14, bolt assembly 16 and
seal gland 18. It is to be understood that both seat member 12 and
heel member 14 can extend away from the interface region, shown in
FIG. 1, for any preferred distances.
[0022] As can be understood from FIGS. 1-4, seat member 12 is
preferably spherical in cross-sectional shape; that is, seat member
12 preferably is disposed uniformly and circumferentially about
axis 20. Additionally, seat member 12 includes a concave portion;
this portion will be described in greater detail below. Preferably,
seat member 12 also possesses seat member duct radius, R.sub.SD,
and seat member spherical radius, R.sub.SS. Seat member duct
radius, R.sub.SD, corresponds to the radius of the inside of seat
member 12, as described more fully below.
[0023] In a preferred embodiment, seat member 12 is made of Inconel
718.TM., which is a high-strength nickel-based alloy capable of
containing the operating pressure and loads at the temperature
extremes experienced by spherical flange assembly 10. However, it
is nevertheless contemplated that seat member 12 may be made of any
ducting material, such as, for example, aluminum alloys, stainless
steels, nickel base alloys, high strength superalloys, titanium
alloys or any composite thereof, depending on the application
pressure and temperature.
[0024] Seat member 12 itself is divided into three portions: seat
duct portion 22, concave seat interface portion 24 and seat flange
connection portion 26. Seat duct portion 22 contains channel 28. It
is through channel 28 that gas or liquid flows from seat member 12
to heel member 14; that is, in a direction such that no forward
step protrudes into the flowstream when misaligned (as referenced
by the arrow extending from Ref. No. 28). Concave seat interface
portion 24 is the portion of seat member 12 which comes into
contact with the corresponding interface portion from heel member
14. Finally, seat flange connection portion 26 allows seat member
12 to be conjoined with heel member 14, through the use of nut and
bolt assembly 16.
[0025] To facilitate the joining of seat member 12 with heel member
14, disposed within seat flange connection portion 26 of seat
member 12 are a plurality of openings 30. Preferably, each of the
plurality of openings 30 are bored, drilled or otherwise cut
through seat connection portion 24 of seat member 12. Further, each
of the plurality of openings 30 are aligned, in both number and
spacing, with a plurality of openings 46 in the heel flange connect
portion 42 of heel member 14.
[0026] As illustrated by FIGS. 1-4, channel 28 is defined by inside
surface 34. Inside surface 34 of channel 28, as shown, also is
disposed uniformly about axis 20. Thus, consequently, inside
surface 34 of channel 28 represents a constant flow area of seat
duct portion 22 of seat member 12.
[0027] Like seat member 12, heel member 14 is preferably also
spherical in cross-sectional shape, also being disposed uniformly
and circumferentially about axis 20, the same axis about which seat
member 12 is disposed. Preferably, heel member 14 also possess heel
member spherical radius, R.sub.HS. Heel member spherical radius,
R.sub.HS, which corresponds to the radius of the conveyance of heel
member 14, is preferably approximately 1.5 to 2.5 times heel member
duct radius, R.sub.HD, which corresponds to the radius of the
inside heel member 12, as described more fully below. This ratio
between heel member spherical radius, R.sub.HS, and heel member
duct radius, R.sub.HD, of heel member 14 serves to preferably
accomplish approximately a 45.degree. nesting interface of heel
member 14 into seat member 12. Alternatively, heel member 14 may
comprise any other spherical radius-shaped device that can
nevertheless realize the objects of the present invention.
[0028] It should be noted that axis 20 is common to both seat
member 12 and heel member 14. Further, seat member duct radius,
R.sub.SD, heel member duct radius, R.sub.HD, seat member spherical
radius, R.sub.ss and heel member spherical radius, R.sub.HS, are
all based from points located along axis 20. As a result, in some
instances, seat member duct radius, R.sub.SD, and heel member duct
radius R.sub.HD, preferably comprise equal values. It should also
be noted that heel member spherical radius, R.sub.HS, and seat
member spherical radius, R.sub.ss, preferably comprise the same
length. This is because the curvature of heel member 14 is equal to
the curvature of seat member 12.
[0029] In a preferred embodiment, heel member 14 is also made of
Inconel 718.TM., which is a high-strength nickel-based alloy
capable of containing the operating pressure and loads at the
temperature extremes experienced by spherical flange assembly 10.
However, it is nevertheless contemplated that heel member 14 may be
made of any ducting material, such as, for example, aluminum
alloys, stainless steels, nickel base alloys, high strength
superalloys, titanium alloys or any composite thereof, depending on
the application pressure and temperature.
[0030] Also similar to seat member 12, heel member 14 itself is
also divided into three portions: heel duct portion 38, convex heel
interface portion 40 and heel flange connection portion 42. Heel
duct portion 38 contains channel 44. Like channel 28, it is through
channel 44 that gas or liquid is permitted to pass from seat member
12 to heel member 14 (again, refer to the direction of the arrow
extending from Ref. No. 44). Convex heel interface portion 40 is
the portion of heel member 14 which comes in contact, through,
preferably, nesting, with the corresponding portion from seat
member 12. Finally, heel flange connection portion 42 allows heel
member 14 to be conjoined with seat member 12, through the use of
nut and bolt assembly 16.
[0031] To facilitate the joining of seat member 12 with heel member
14, disposed within heel flange connection portion 42 of heel
member 14 are a plurality of openings 46. Preferably, each of the
plurality of openings 46 are bored, drilled or otherwise cut
through heel connection portion 42 of heel member 14. Further, each
of the plurality of openings 46 are aligned, in both number and
spacing, with the plurality of openings 30 in the seat flange
connect portion 26 of seat member 12.
[0032] As illustrated by FIGS. 1-4, channel 44 is defined by inside
surface 50. Inside surface 50 of channel 44, as shown, also is
disposed uniformly about axis 20. Thus, consequently, inside
surface 50 of channel 44 is preferably a constant flow area of heel
duct portion 38 of heel member 14.
[0033] As channel 44 approaches convex heel interface portion 40,
inside surface 50 of channel 44 is beveled outward, as shown by
reference numeral 70. The purpose for the beveling 70 of inside
surface 50 of channel 44 is selected to preclude a forward facing
step from protruding into the flow stream with the maximum
prescribed angular misalignment.
[0034] Additionally disposed within heel member 14 is seal gland
opening 54. As illustrated in FIGS. 1-4, seal gland opening 54 is
disposed within first heel interface portion 40 of heel member 14.
Seal gland opening 54 is preferably configured to receive seal
gland 18. Seal gland 18 is preferably used to provide a zero
leakage seal between seat member 12 and heel member 14. Preferably,
seal gland 18 may comprise an o-ring for room temperature
application or a metal pressure actuated seal with appropriate
coating for cryogenic or hot gas applications.
[0035] As illustrated by FIG. 2, width 66, preferably specified in
degrees, of convex heel interface 40 is preferably greater than
width 68 of seal gland opening 54, also preferably specified in
degrees, plus two times the degrees of a predetermined allowable
misalignment. This is such that seal gland 18 will always be seated
on the spherical surface of convex heel interface portion 40 when
spherical flange assembly 10 is misaligned.
[0036] As illustrated in FIG. 1, and part of spherical flange
assembly 10 is bolt assembly 16. As illustrated, bolt assembly 16
comprises bolt 56, bolt spherical washer 58, nut 60 and nut
spherical washer 62. Each bolt assembly 16 are disposed within two
of the plurality of openings 30, 46. In operation, when each bolt
assembly 16 is installed within one of the plurality of openings
30, and a corresponding opening 46, bolt assembly 16 is tightened,
thereby nesting heel member 14 into seat member 12. Each element of
bolt assembly 16 comprises elements commonly known in the art,
although it is preferred that each element comprises compatible
strength materials to permit preloading spherical flange assembly
10 with sufficient preload to preclude separation at the nested
interfaces of heel member 14 and seat member 12 at maximum
operating conditions.
[0037] Further, each of the plurality of openings 30, 46 are
configured in a manner to receive bolt 56 of bolt assembly 16. That
is, each of the plurality of openings 30, 46 are of a diameter
large enough to permit the prescribed angular misalignment without
binding bolt 56 of bolt assembly 16. It is further preferred that
the inside surfaces 32, 48 of each of the plurality of openings 30,
46, respectively, comprise a smooth, unthreaded surface to allow
bolt 56 of bolt assembly 16 to pass through each of the plurality
of openings 30, 46 and be retained by nut 60 of bolt assembly
16.
[0038] FIG. 5 illustrates spherical flange apparatus 10 in
operation. Referring to FIG. 5, heel member 14 is illustrated as
being misaligned from seat member 12. The axis of seat member 12 is
illustrated as reference numeral 72, while the axis of heel member
is shown as reference numeral 74. The angle of deflection between
the seat member 12 and the heel member 14 is illustrated by
.alpha.. As can be seen from FIG. 5, although there is misalignment
between seat member 12 and heel member 14, spherical flange
assembly 10 does not cause leakage of any gas or liquid contained
therewith. Also illustrated in FIG. 5 is an axial space 76. Axial
space 76 is provided between seat member 12 and heel member 14 to
permit a predetermined amount of angular misalignment by rotating
on the nested spherical interface without bottoming on the flange
faces. Also shown in FIG. 5 is the spacing between bolt assembly
106 and the plurality of openings 30, 46.
[0039] While specific embodiments of the present invention have
been described in detail, it will be appreciated by those skilled
in the art that various modifications and alternatives to those
details could be developed in light of the overall teachings of the
disclosure. Accordingly, it will be understood that the particular
arrangements and procedures disclosed are meant to be illustrative
only and not limiting as to the scope of the invention, which is to
be given the full breadth of the appended claims and any
equivalents thereof.
* * * * *