U.S. patent number 3,867,065 [Application Number 05/379,677] was granted by the patent office on 1975-02-18 for ceramic insulator for a gas turbine blade structure.
This patent grant is currently assigned to Westinghouse Electric Corporation. Invention is credited to Claude R. Booher, Jr., Thomas J. Rahaim, Richard J. Schaller.
United States Patent |
3,867,065 |
Schaller , et al. |
February 18, 1975 |
CERAMIC INSULATOR FOR A GAS TURBINE BLADE STRUCTURE
Abstract
A stationary ceramic three-piece blade structure for gas
turbines has an annularly shaped ceramic insulator disposed on its
outer periphery. An annularly shaped ceramic insulator is disposed
on the inner side of the inner periphery of the blade structure.
The ceramic insulators maintain required heat patterns within the
three-piece ceramic blade members. The ceramic insulators also
prevent heat and thermal gradients from damaging the three piece
stationary blade structure and the metal members which surround and
support the stationary blade structure in the turbine.
Inventors: |
Schaller; Richard J. (Ambler,
PA), Rahaim; Thomas J. (Claymont, DE), Booher, Jr.;
Claude R. (West Chester, PA) |
Assignee: |
Westinghouse Electric
Corporation (Pittsburgh, PA)
|
Family
ID: |
23498216 |
Appl.
No.: |
05/379,677 |
Filed: |
July 16, 1973 |
Current U.S.
Class: |
415/209.4;
415/200 |
Current CPC
Class: |
F01D
9/042 (20130101); F01D 5/284 (20130101); F05D
2240/10 (20130101); F05D 2300/21 (20130101) |
Current International
Class: |
F01D
5/28 (20060101); F01D 9/04 (20060101); F01d
009/02 () |
Field of
Search: |
;415/200,214,216,217,219R,218 |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
Other References
Publication, "Ceramics"-Key to the Hot Turbine Gas Turbine
International, Jan.-Feb. 1973, pages 30-36..
|
Primary Examiner: Raduazo; Henry F.
Attorney, Agent or Firm: Baehr, Jr.; F. J.
Claims
1. A hot elastic fluid stator blade construction for a gas turbine,
comprising a plurality of radially directed stationary ceramic
blades disposed across an annularly shaped hot fluid flow path,
each of said stationary ceramic blades being supported on their
radially inner ends by a ceramic inner end cap, each of said
stationary ceramic blades being supported on their radially outer
ends by a ceramic outer end cap, said ceramic outer end caps
defining a portion of the radially outer surface of said annularly
shaped hot fluid flow path, said inner ceramic end caps defining a
portion of the radially inner surface of said annularly shaped hot
fluid flow path, and an arcuately shaped ceramic insulator disposed
on the radially outer side of said outer ceramic end caps, and an
arcuately shaped ceramic insulator disposed on the radially inner
side of the inner ceramic end caps, said ceramic insulators
preventing damage to said end caps from thermal distortion caused
by uneven temperature distribution therein, said ceramic insulators
having a woven fibrous ceramic material
2. A hot elastic fluid stator blade construction as recited in
claim 1, wherein said woven fibrous ceramic material has a directed
orientation within said ceramic insulators to reduce thermal
conductivity through the ceramic insulators in the radial
direction, and to add structural strength to the ceramic
insulators.
Description
BACKGROUND OF THE INVENTION
1. Field of the Invention
This invention relates generally to gas turbines, and more
particularly to ceramic insulators disposed about a plurality of
radially directed stationary ceramic three-piece blade structures
in a gas turbine for reducing any damaging properties of heat that
may effect the blade structures, and their metal support
members.
2. Description of the Prior Art
The efficiency of gas turbines can be increased markedly over
present turbomachines, by increasing the hot motive fluid working
temperature. To operate at high temperatures; however, components
within and surrounding the hot motive fluid flow path, must be able
to withstand very high temperatures. These temperatures are in the
vicinity of 2,500.degree.F. Turbine designers have created turbine
blades using ceramic materials which can withstand this high
temperature. Supporting end caps of ceramic material are also
necessary to withstand the high temperatures and to maintain the
ceramic blades in place. However, these ceramic end caps do not
provide enough insulation to prevent the high temperatures of the
motive fluid from effecting the surrounding metal components, and
some means is also needed to prevent large thermal gradients from
damaging the end caps themselves. Cooling air, at temperatures of
650.degree.F, for cooling the supporting metal structure, is used
to reduce the damaging effects of the heat emanating from the hot
motive fluid flow path. This means a temperature drop of
1,850.degree.F between the inside hot face of the supporting
ceramic end caps and the adjacent metal structure in which the end
caps are supported. Severe thermal distortions will take place in
the end caps, due to the high linear and non-linear thermal
gradients within the end caps. The supporting elements will also be
affected by the high temperatures and non-linear thermal gradients.
The high temperatures and thermal distortions will cause the metal
components near the hot motive fluid path to have a short life.
Accordingly, it is one object of the present invention to provide a
novel and improved insulating structure around the ceramic blades
in a gas turbine.
It is another object of the invention to provide a novel and
improved structure for maintaining metal components near the hot
motive fluid path at lower temperatures and in a non-distorted
state.
Accordingly, it is one object of the present invention to provide a
novel and improved insulating structure around the ceramic blades
in a gas turbine.
It is another object of the invention to provide a novel and
improved structure for maintaining metal components of gas turbine
at lower temperatures and in a non-distorted state.
SUMMARY OF THE INVENTION
In accordance with this invention, the turbine is provided with an
annular row of ceramic blades, each blade having ceramic inner and
ceramic outer supporting end caps, and a metal shroud structure
supporting the end cap members. The shroud structure consists of an
annular series of arcuate segments which are on the outermost
portion of the radially outward end caps and an annular series of
arcuate segments which are on the innermost portion of the radially
inward end caps. The shroud members are arranged in end-to-end
abutment with each other. An insulating member is disposed on the
blade side of each inner and outer shroud and adjacent the shrouds.
The insulating member which is made from a ceramic insulating
material may be comprised of a generally uniform ceramic material,
or it may have a directionally oriented fibrous ceramic material
interwoven within the ceramic body insulator member. The ceramic
insulator is actually a portion of the shroud. The ceramic material
insulator portion of the shroud member has low thermal conductivity
compared to the thermal conductivity of the ceramic blades and the
supporting ceramic end caps.
The temperature drop across the ceramic insulator is large, and
therefore it will extend the life of the ceramic end caps and
blades by minimizing non-linear thermal gradients within the blades
and caps and it will extend the life of the supporting metal
shrouds and turbine components disposed about the ceramic insulator
in the gas turbine by reducing the heat flow to those
components.
BRIEF DESCRIPTION OF THE DRAWINGS
Reference may be had to the following drawings for a better
understanding of the nature and the objects of the invention, in
which:
FIG. 1 is a radial sectional view of a portion of an inner and an
outer shroud comprising fibrous ceramic insulators, with a
plurality of ceramic blades and supporting end caps therebetween,
constructed according to the principles of this invention; and,
FIG. 2 is a view in perspective, of a portion of a bladed structure
showing the fibrous ceramic insulators.
FIG. 3 is a radial sectional view similar to FIG. 1 showing the
invention using solid ceramic insulators.
FIG. 4 is a view similar to FIG. 2 showing the invention using
solid ceramic insulators.
DESCRIPTION OF THE PREFERRED EMBODIMENTS
Referring to the drawings in detail, and particularly to FIG. 1,
there is shown a portion of a turbine diaphragm structure 10,
comprising an annularly disposed inner shroud member 12, an
annularly disposed outer shroud member 14, and a plurality of
radially extending stationary ceramic blades 16, each blade having
a radially inner end 17 and a radially outer end 19, supported and
disposed therebetween. Although the entire diaphragm structure 10
is not shown, it will be understood that the shroud members, 12 and
14, are of circular cross section, and the blades 16 are arranged
in an annular circumferential array between the inner and outer
shroud members.
The ceramic blades 16 each have a ceramic supporting end cap 18 at
both their radially inner end 17 and their radially outer end 19. A
ceramic insulator 20 is annularly disposed radially inwardly of the
inner ceramic end caps 18, between the inner end cap 18 and a metal
portion 22 of the inner shroud member 12. The overall inner ceramic
insulator 20 may comprise a plurality of arcuate segments 21 in end
to end abutment with each other, while still maintaining their
circumferential disposition. The arrangement of the outer shroud
member 14 may be the same as that for the inner shroud member 12. A
ceramic insulator 24 is annularly disposed radially outwardly of
the outer ceramic end caps 18. The overall outer ceramic insulator
24 may also comprise a plurality of arcuate segments 23 in end to
end abutment with each other, while still maintaining their
circumferential disposition. The outer ceramic insulator 24 is
disposed between the outer end caps 18 and a metal portion 26 of
the outer shroud 14.
One embodiment of the ceramic insulators, 20 and 24, comprises a
ceramic fiber 28, interwoven within the ceramic insulator members,
20 and 24, as shown in FIGS. 1 and 2. The ceramic fiber 28 may be
comprised of zirconium oxide, fused quartz or fused silica. The
ceramic fiber 28 reinforces the ceramic insulators 20 and 24,
and/or the ceramic fiber 28 may give a directional preference to
certain properties of the ceramic material. For example, the
ceramic fiber 28 may have a specific weave to give the insulator
members, 20 and 24, a low thermal conductivity in the radial
direction thereby causing a reduction in the heat loss from the hot
motive fluid flow path, and also causing a reduction in the thermal
gradients across the end caps 18 that support the ceramic blades
16. Additionally, a ceramic fiber 28 interwoven within the ceramic
insulators, 20 and 24, would allow the insulators, 20 and 24, to be
more compatible to thermal distortions than would a solid
insulator, and therefore, would be less susceptible to thermal
bending stresses.
As also shown more clearly in FIG. 2, a hole 29 is disposed within
the insulators, 20 and 24, radially inwardly of and radially
outwardly of each of the end caps 18, as part of an arrangement for
providing a compressive force upon the ceramic blade 16 and the
ceramic end caps 18. Holes 29 that are disposed in the ceramic
insulator members, 20 and 24, that have a fibrous ceramic material
28 interwoven therein, are not as critical from a point of view of
stress concentrations as are solid ceramic insulator members, 20
and 24, without any ceramic fiber 28 woven therein, as shown in
FIGS. 3 and 4.
The diaphragm structure 10, shown in FIGS. 3 and 4, is similar to
the diaphragm structure 10 shown in FIGS. 1 and 2, except that the
FIGS. 3 and 4 show insulators, 20 and 24, that do not include any
fibrous ceramic 28 therein; that is, they are generally a solid
uniform ceramic. The embodiment shown in FIGS. 3 and 4 also do not
have holes in the insulators, 20 and 24. The solid non-fibrous
ceramic insulators 20 and 24 may be comprised of lithium aluminum
silicate. The non-fibrous insulators, 20 and 24, are characterized
by low thermal stresses, high wear resistance and load bearing
capabilities.
The purpose of the fibrous or solid non-fibrous ceramic insulator
members, 20 and 24, is however, to provide a large temperature drop
between each ceramic end cap 18 and the metal portions, 22 and 26,
of the inner and outer shroud members, 12 and 14. A large
temperature drop is required because the stationary ceramic blades
16 and the ceramic end caps 18 may be constructed from silicon
carbide, SiC, or silicon nitride, Si.sub.3 N.sub.4, both of which
have a thermal conductivity (K) of about 10 to 65
BTU/hr.-ft.-F.degree., for a temperature range from 2,500.degree.F
down to ambient temperature. Temperatures of about 2,500.degree.F
will be necessary in the stationary inlet vanes of gas turbines if
they are to achieve a high efficiency and power output. Without an
insulator on the radially inner and radially outer side of each
radially inner and radially outer end cap, 18 respectively, the
ceramic end caps 18 would be subject to a gas temperature of about
2,500.degree.F on their side nearest the hot motive fluid flow
path, and to a temperature of about 650.degree.F caused by cooling
air impinging upon their side radially furthermost from the hot
motive fluid flow path. A temperature drop of 1,850.degree.F across
the ceramic end caps 18 would result in severe thermal distortions
and large steady state and transient thermal stresses within the
ceramic end caps 18. Also large bending stresses would occur in the
ceramic end caps 18 if the temperature gradient across them were
non-linear, which is the situation for both the transient and the
steady state turbine operation. The metal shroud members, 22 and
26, adjacent the ceramic end caps 18 would be subject to high
temperatures, thermal distortions and bending stresses were it not
for the disposition of ceramic insulators, 20 and 24, therebetween,
having low thermal conductivity. The ceramic insulators, 20 and 24,
prevent high thermal gradients from extending across the end caps
18, and the ceramic insulators, 20 and 24, prevent damaging
temperatures within the metal portions, 22 and 26, of the
surrounding shroud members 12 and 14.
Since numerous changes may be made in the above-described
construction, and different embodiments may be made without
departing from the spirit and scope thereof, it is intended that
all matter contained in the foregoing description or shown in the
accompanying drawings shall be interpreted as illustrative and not
in a limiting sense.
* * * * *