U.S. patent number 3,910,716 [Application Number 05/472,753] was granted by the patent office on 1975-10-07 for gas turbine inlet vane structure utilizing a stable ceramic spherical interface arrangement.
This patent grant is currently assigned to Westinghouse Electric Corporation. Invention is credited to Stephen D. Leshnoff, Jeffrey D. Roughgarden.
United States Patent |
3,910,716 |
Roughgarden , et
al. |
October 7, 1975 |
Gas turbine inlet vane structure utilizing a stable ceramic
spherical interface arrangement
Abstract
An improved ceramic inlet vane structure for axial flow gas
turbines, comprising an array of three ceramic blades arranged in a
vane segment. Each blade has a spherical interface between its
radially inner and outer ends and their respective supportive end
caps. The three points of contact between the inner ends of the
three blades and their respective inner end caps in the vane
segment generally define a triangle. The points of contact between
the outer ends of each the three blades and their respective outer
end caps in the vane segment also generally define a triangle. Each
group of inner and outer end caps themselves are restrained by a
shoe having a single spherical interface with inner and outer
shroud members respectively. The four spherical interface points on
the inner portions and on the outer portions of each vane segment
define a tetrahedron. This configuration provides high stability
with a slight freedom of movement within each vane segment and a
slight freedom of movement within each blade. An annular arrray of
vane segments comprises the inlet nozzle of a gas turbine.
Inventors: |
Roughgarden; Jeffrey D. (Palo
Alto, CA), Leshnoff; Stephen D. (Highland Park, NJ) |
Assignee: |
Westinghouse Electric
Corporation (Pittsburgh, PA)
|
Family
ID: |
23876805 |
Appl.
No.: |
05/472,753 |
Filed: |
May 23, 1974 |
Current U.S.
Class: |
415/209.2;
415/200; 415/217.1; 415/138; 415/189; 415/209.4 |
Current CPC
Class: |
F01D
9/042 (20130101); F05D 2250/241 (20130101); F05D
2300/21 (20130101) |
Current International
Class: |
F01D
9/04 (20060101); F01D 009/02 () |
Field of
Search: |
;415/134,136,138,139,217,218,219 |
References Cited
[Referenced By]
U.S. Patent Documents
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|
|
3066911 |
December 1962 |
Anderson et al. |
3843279 |
October 1974 |
Crossley et al. |
|
Foreign Patent Documents
|
|
|
|
|
|
|
826,673 |
|
Jan 1952 |
|
DT |
|
832,301 |
|
Apr 1960 |
|
GB |
|
Primary Examiner: Raduazo; Henry F.
Attorney, Agent or Firm: Winans; F. A.
Government Interests
The invention herein described was made in the course of or under a
contract or subcontract thereunder, with the Department of Defense.
Claims
We claim:
1. An inlet nozzle for a gas turbine having a radially inner shroud
ring, a radially outer shroud ring coaxial with said inner shroud
ring, and an annular array of vane segments compressively retained
therebetween, each of said vane segments comprising:
a. three radially extending ceramic blades;
b. three separate outer supportive end caps forming an outer
arcuate segment;
c. three separate inner supportive end caps forming an inner
arcuate segment;
d. a first support means extending across said outer arcuate
segment for retaining said outer end caps in proper orientation,
with each end cap in opposed facing relationship to the radially
outer end of a blade;
e. a second support means extending across said inner arcuate
segment for retaining said inner end caps in proper orientation,
with each end cap in opposed facing relationship to the radially
inner end of a blade;
f. means providing a ball and socket engagement between said first
support means and said outer shroud ring generally midway between
the arcuate extent of said support means;
g. means providing a ball and socket engagement between said second
support means and said inner shroud ring generally midway between
the arcuate extent of said second support means;
h. means providing a ball and socket engagement between each end
cap and the adjacent radial end of the blade associated
therewith;
i. said ball and socket engagements between each of the three
blades and their respective outer end caps being disposed such that
each point of engagement determines a vertex of a first included
triangle;
j. said ball and socket engagements between each of the three
blades and their respective inner end caps being disposed such that
each point of engagement determines the vertex of a second included
triangle; and wherein,
k. said vertices of said first included triangle in conjunction
with said ball and socket engagement of said outer shroud to said
support means define a substantially stable tetrahedral
relationship between the points of engagement for the radially
outer support of each vane segment; and,
l. said vertices of said second included triangle in conjunction
with said ball and socket engagement of said inner shroud to said
inner support means define substantially stable tetrahedral
relationship between the points of engagement for the radially
inner support of each vane segment.
Description
BACKGROUND OF THE INVENTION
1. Field of the Invention
This invention relates generally to turbines, and more particularly
to ceramic inlet nozzle structures for gas turbines.
2. Description of the Prior Art
Gas turbines presently employ integral first stage metal inlet vane
segments. As inlet temperatures are increased to increase turbine
efficiency, cooling of the metal inlet vanes is necessary.
Providing cooling fluid for the metal vanes utilizes some of the
power produced by the turbines, hence it decreases the overall
efficiency of that unit. Ceramics have been introduced as a high
temperature material from which to construct the inlet vane
segments. Ceramics, however, are structurally most stable when used
in a compressed state. Gas turbine inlet nozzles during operation
have an array of forces generated therein that are not strictly
compressive. The forces generated therein may be in shear or
tension, and are produced because of thermal expansion, movement of
adjacent members, and the like.
An object of this invention is to overcome the problems associated
with the prior art.
Another object of this invention is to design a structural
arrangement within the inlet nozzle so that those forces generated
within the ceramic blades and supportive end caps will be of
minimal deleteriousness.
Yet another object of this invention is to provide a stable vane
segment arrangement that will permit a slight freedom of elongation
and rotation for the individual blades within that vane
segment.
SUMMARY OF THE INVENTION
In accordance with the present invention, there is provided an
improved inlet nozzle structure for a gas turbine. Vane segments,
an annular array of which comprise the inlet nozzle, themselves are
comprised of three radially directed ceramic blades. Each blade has
its own supportive radially inner and radially outer ceramic end
cap. Each radial end of each of the ceramic blades has a generally
hemispherical cavity disposed within it. Each adjacent ceramic end
cap has a generally hemispherical cavity aligned with its
respective cavity in its radially adjacent blade. A ceramic sphere
is disposed in each cavity between each of the ceramic blades and
each ceramic end cap. This provides a spherical interface
therebetween. The ceramic sphere permits slight freedom of pivotal
motion of the blades with respect to one another and with respect
to the vane structure itself. Each array of radially inner spheres
and each array of radially outer spheres define corners of a
triangle. Each array of end caps is restrained by a shoe having a
spherical interface with its respective inner and outer shroud. The
four inner and four outer points of spherical interface each define
a tetrahedron. The radially outer vertex of the outer tetrahedron
being compressed radially inwardly, all of the spherical interface
points providing a support arrangement that is very stable, and
which also permits slight elongation and rotation of its
components.
BRIEF DESCRIPTION OF THE DRAWINGS
For a better understanding of the nature of the invention,
reference may be had to the following detailed description, taken
in conjunction with the accompanying drawings, in which:
FIG. 1 is an exploded perspective view of a portion of an inlet
nozzle of a gas turbine, showing a vane segment constructed in
accordance with the principles of this invention;
FIG. 2 is a schematic diagram of a three blade stable vane assembly
utilizing a spherical interface arrangement;
FIG. 3 is a longitudinal sectional view of the middle blade and
spherical interface support arrangements of the stable vane
assembly;
FIG. 4 is a longitudinal sectional view of an end blade in a vane
segment and a spherical interface arrangement for the blades in a
vane segment;
FIG. 5 is another embodiment of a spherical interface arrangement
for the blades in a vane segment;
FIG. 6 is yet another embodiment of a spherical interface
arrangement for the blades on a vane segment;
FIG. 6a is still another embodiment of a spherical interface
arrangement for the blades on a vane segment; and,
FIG. 7 is a stop arrangement for preventing excessive twist in each
blade.
DESCRIPTION OF THE PREFERRED EMBODIMENTS
Referring to the drawings, and particularly to FIG. 1, there is
shown a portion of an inlet arrangement of an axial flow gas
turbine 10 having a stable inlet nozzle arrangement 12.
The gas turbine 10 includes a turbine axis 14, an outer cylinder
16, an annular array of vane segments 18 which comprise the inlet
nozzle arrangement 12, and at least one rotor disc 20 with an array
of rotating blades 22. A fixed plunger biasing arrangement 23 is
disposed radially outwardly of each array of vane segments 18 to
maintain each array of vane segments 18 in a generally compressed
state.
The vane segments 18 are preferably constructed from ceramic
materials, to withstand the high temperatures, about 2500.degree.F,
which exist within the inlet nozzle 12 due to the flow of hot gases
therethrough from an array of combustion chambers, not shown. The
vane segments 18 are maintained in the compressed state because
ceramic materials are strongest in that mode.
The vane segments 18 are comprised of three individual ceramic
airfoil blades 24, each blade 24 having its own supportive radially
inner ceramic end caps 26, and their own radially outer ceramic end
caps 28. An insulator and supportive member 30 is disposed radially
outwardly of the outer ceramic end caps 28 and an insulator and
supportive member 32 is disposed radially inwardly of the inner
ceramic end caps 26.
Each end of each ceramic blade has a spherical interface
arrangement 25 with its respective adjacent ceramic end cap 26 or
28. The preferred embodiment discloses a rolling spherical
interface relationship with each blade 24 and respective end caps
26 and 28, that comprise, with a spherical pivot assembly 27 and
27', radially outwardly and inwardly respectively, of the outer and
inner supportive members 30 and 32, a stable vane assembly 12.
The radially outer end of each ceramic blade 24 has a generally
hemispherical cavity 34 disposed therein, as shown in FIGS. 1, 3
and 4. Each outer ceramic end cap 28 also has a generally
hemispherical cavity 36 disposed therein, radially adjacent the
cavity 34. A generally spherical ceramic member 38 is disposed
between the two outer hemispherical cavities 34 and 36, and
supportively maintained therebetween. The radially inner end of
each ceramic blade 24 has a generally hemispherical cavity 40
disposed therein. Each inner ceramic end cap 26 also has a
generally hemispherical cavity 42 disposed therein, radially
adjacent the cavity 40 in the radially inner end of the blade 24. A
generally spherical ceramic member 44 is disposed between the two
inner hemispherical cavities 40 and 42, and supportively maintained
therebetween.
The arrangement of the radially inner cavities 40 and 42 and their
respective ceramic spheres 44 generally form the points of a
triangle, the sides of which are indicated by dotted lines and the
letters A, B and C on FIG. 2. A similar non-linear arrangement of
the radially outer cavities 34 and 36 is also shown in FIG. 2,
labeled A'.sub.1, B'.sub.1 and C'.sub.1. The radially inner and
outer spherical interlock arrangements 25 each form a tetrahedron
with spherical pivots 27' and 27, respectively. The radially inner
and outer tetrahedrons, defined by A.sub.2 B.sub.2 C.sub.2 D and
A'.sub.1 B'.sub.1 C'.sub.1 D' respectively, are each loaded in
compression, due to the action of biasing member 23, and are able
to pivot slightly about each radially extreme vertex, D and D'.
The use of three blades 24 in each vane segment 18 permits the use
of spherical interfaces in a generally triangular arrangement as
stated above. This triangular arrangement permits each vane segment
18 to bend unrestrained about any axis. Collapse of the three
blades 24 in the vane segment 18 in the axial or circumferential
direction cannot occur, since this would require a parallel
displacement by the two planes defined by A.sub.2 B.sub.2 C.sub.2
and A'.sub.1 B'.sub.1 C'.sub.1, which however, is prevented by the
fixed plunger biasing arrangement 23, mentioned earlier, to help
keep each entire vane segment 18 in compression. Collapse by
relative rotation of the two tetrahedrons defined by A.sub.2
B.sub.2 C.sub.2 D and A'.sub.1 B'.sub.1 C'.sub.1 D', cannot occur
since it would be stopped by compression of any of the three blades
24. The relationship of the axial positioning of the spherical
interfaces for the individual blades 24, is shown in FIGS. 3 and 4.
FIG. 3 showing the middle blade 24 in each vane segment 18, and
FIG. 4 showing an end blade 24 in each three blade vane segments.
The non-linearity of the middle blade spherical interface 25 with
respect to the end blade spherical interfaces 25 is shown in FIG.
1, and can be seen by comparing the axial displacement of the
spherical interfaces 25 of FIGS. 3 and 4.
Each pivotable assembly 27 or 27', or radially extreme inner or
outer vertex is a spherical interface, one part of each pivotable
assembly being on the supportive member 30 and 32, or load plate,
the other part being disposed on the outer or inner housing rings
39 and 37 respectively. The supportive members, 30 and 32 include
hemispherical tenons 31 which pivotably mate with hemispherical
cavities 33. The tenons 31 and cavities 33 comprise part of the
spherical pivot assemblies 27 and 27'.
An alternative embodiment of the spherical interface is shown in
FIG. 5. A single ceramic airfoil blade 46 from a vane segment 18 is
shown disposed between an inner ceramic end cap 48, and an outer
ceramic end cap 50. The load plates or supportive members 30 and 32
are similar to the earlier shown embodiment. Each ceramic end cap
48 and 50 has a generally hemispherical cavity 52 disposed therein.
The ceramic airfoil blade 46 has a generally hemispherical tenon 54
on both the radially inner and outer ends, disposed radially
adjacent each cavity 52 in the end caps 48 and 50. The tenon 54
mates with each cavity 52 in their respective end caps 48 and 50.
The non-linear or generally triangular arrangement of the spherical
interfaces between the blades 46 and end caps 48 and 50 would be
the same as that shown in FIGS. 1 and 2. A biasing means, 23, as
shown in FIGS. 1 and 2, would provide a compressive force on each
vane segment 18 having either the independent ceramic spheres 38
and 44, between the blade 24 and end caps 26 and 28, or the
embodiment using a tenon 54 mating with cavities 52 in the end caps
48 and 50. One of the tensons 54 shown in FIG. 5, could be a
ceramic sphere. The support arrangement would then be a combination
of the embodiments of FIGS. 4 and 5, as shown in FIG. 6a.
Another possible embodiment, shown in FIG. 6 utilizes the
disposition of a tenon 56 on each end cap 58 itself, mating with
hemispherical cavities 60 on each end of an airfoil blade 62. Yet
another embodiment shown in FIG. 6a, utilizes a tenon 72 and
hemispherical cavity 74 arrangement between one end of a blade 75
and end cap 76, and a ceramic sphere 78 and two hemispherical
cavities 79 and 81 in the blade 75 and other associated end cap
80.
With any of the above disclosed embodiments of interfacing, a
ceramic stop 64 may be used. The ceramic stop 64 is a sphere having
a quadrant removed. The stop 64 is restrained in a cavity 66 in an
inner or outer end cap 68. The stop 64 being bonded to the end cap
68. A blade 69, before excessive twisting, will come into contact
with wall portions 70 of the stop 64, and prevent failure of the
blade 69 or collapse of the vane segment 18. The use of vane
segments 18 described, in any case, require a different number of
those vane segments 18 in a nozzle arrangement 12 than are usually
present in the prior art. Additionally, the use of more support
members 30 and 32, eliminate troublesome leakage paths, dangerous
harmonics, and would reduce the number of seals required. It is
understood that each alternative support embodiment utilizes the
generally tetrahedronal pattern of support points in the assembled
vane segment, and the triangular pattern of support points between
the blades and their end caps.
The contact surfaces of the spherical interfaces have the advantage
that they permit rotation in three directions, of each blade. The
rotation may be caused by: compressive spring loading -- a normal
load; gas loading -- tangential load; and gas twisting moment -- a
twist load. The linkage stability realized through the arrangement
of spherical interfaces disposed in tetrahedral arrays as disclosed
above is insured with this configuration.
It will be apparent to those skilled in the art, after having had
the benefit of this invention, that other embodiments are possible,
and are so included within the scope of the claims.
* * * * *