U.S. patent application number 14/417945 was filed with the patent office on 2015-06-18 for combustion chamber cooling.
The applicant listed for this patent is SIEMENS AKTIENGESELLSCHAFT. Invention is credited to Olga Deiss, Thomas Grieb, Matthias Hase, Jens Kleinfeld, Bernd Prade.
Application Number | 20150167978 14/417945 |
Document ID | / |
Family ID | 48652044 |
Filed Date | 2015-06-18 |
United States Patent
Application |
20150167978 |
Kind Code |
A1 |
Deiss; Olga ; et
al. |
June 18, 2015 |
COMBUSTION CHAMBER COOLING
Abstract
A gas turbine combustion chamber (8) surrounded by an inner wall
(2) having cooling air bores (17) and an outer wall (9) that is
spaced from the inner wall (2). The outer wall (9) likewise has
cooling air bores (16) and is formed of a plurality of wall
elements (11) that are arranged in the circumferential direction of
the gas turbine combustion chamber (8) essentially next to each
other. The outer wall elements are arranged on the inner wall (2)
by means of a fixed bearing (24) on one narrow side (21) of a wall
element and by means of a floating bearing (25) on an opposite
narrow side (21) of the element, configured to define a hollow
space (10) is formed between the two walls (2, 9).
Inventors: |
Deiss; Olga; (Dusseldorf,
DE) ; Grieb; Thomas; (Krefeld, DE) ; Hase;
Matthias; (Mulheim, DE) ; Kleinfeld; Jens;
(Mulheim an der Ruhr, DE) ; Prade; Bernd;
(Mulheim, DE) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
SIEMENS AKTIENGESELLSCHAFT |
Munchen |
|
DE |
|
|
Family ID: |
48652044 |
Appl. No.: |
14/417945 |
Filed: |
June 12, 2013 |
PCT Filed: |
June 12, 2013 |
PCT NO: |
PCT/EP2013/062148 |
371 Date: |
January 28, 2015 |
Current U.S.
Class: |
60/722 |
Current CPC
Class: |
F23R 3/002 20130101;
F23R 2900/03044 20130101; F23R 3/60 20130101; F23R 3/06 20130101;
F23R 3/04 20130101; F23R 2900/00014 20130101 |
International
Class: |
F23R 3/04 20060101
F23R003/04; F23R 3/00 20060101 F23R003/00 |
Foreign Application Data
Date |
Code |
Application Number |
Aug 2, 2012 |
DE |
102012213637.1 |
Claims
1. A gas turbine combustion chamber comprising: an inner wall
around the chamber, first cooling air bores through the inner wall;
an outer wall around and spaced above the inner wall, second
cooling air bores through the outer wall; the outer wall is formed
from multiple separate wall elements which are arranged
substantially next to one another in the circumferential direction
of the gas turbine combustion chamber, the wall elements having
opposite, axially extending, narrow sides and are spaced above the
inner wall; a respective fixed bearing located on one of the narrow
sides of each wall element and supporting the respective narrow
side of the wall element on and spaced above the inner wall and the
fixed bearing being configured to hold the wall element against
shifting circumferentially; and a floating bearing on the opposite
narrow side of each of the wall elements, the fixed and floating
bearings being configured to support the neighboring wall elements
with respect to the inner wall such that a cavity is formed between
the inner and outer walls; and adjacent wall elements are arranged
such that they overlap in the circumferential direction.
2. The gas turbine combustion chamber as claimed in claim 1,
wherein the outer wall elements are supported on and located above
the inner wall by the fixed bearing toward a burner side of the
wall elements and by the floating bearing on the turbine side of
the wall elements.
3. The gas turbine combustion chamber as claimed in claim 1,
wherein the inner wall is in the form of a hollow frustum and the
wall elements are in the form of hollow frustum segments.
4. The gas turbine combustion chamber as claimed in claim 1,
wherein the floating bearing is comprised of ring segments which
each have a groove located and configured for receiving one narrow
side of adjacent ones of the wall elements and the groove is
configured to allow the respective narrow sides received in the
respective groove to move in the groove due to temperature
variation.
5. The gas turbine combustion chamber as claimed in claim 1,
wherein the fixed bearing is comprised of ring segments around the
inner wall.
6. The gas turbine combustion chamber as claimed in claim 2,
wherein at least one of the bearings has cooling air bores.
7. The gas turbine combustion chamber as claimed in claim 1,
further comprising retainers located in the region where each two
adjacent wall elements overlap and configured to prevent the two
adjacent wall elements from separating.
8. The gas turbine combustion chamber as claimed in claim 7,
wherein the retainers are attached to the inner wall.
9. The gas turbine combustion chamber as claimed in claim 8,
further comprising the wall elements have openings for the
retainers to extend through the openings, and diameters of the
retainer openings in each two adjacent wall elements are larger
than the diameters of the retainers for their adjacent wall
elements.
10. The gas turbine combustion chamber as claimed in claim 1,
further comprising spacers between the inner wall and the outer
wall located to prevent contact between the inner and outer
walls.
11. The gas turbine combustion chamber as claimed in claim 10,
wherein the spacers are arranged on the inner wall and located
opposite a central region of the respective wall element.
12. The gas turbine combustion chamber as claimed in of claim 1,
wherein a cavity is formed between the inner wall and the outer
wall and is embodied as an acoustic damper.
13. The gas turbine combustion chamber as claimed in claim 2,
wherein the floating bearing receives the narrow axial sides of
each two neighboring outer wall elements to overlap in the floating
bearing.
14. The gas turbine combustion chamber as claimed in claim 3,
wherein the floating bearing of each outer wall element is toward a
wider end of the frustum and the fixed bearing of each outer wall
element is toward a narrow end of the frustum.
15. The gas turbine combustion chamber as claimed in claim 2,
wherein the fixed bearing is welded to the inner wall.
Description
CROSS-REFERENCE TO RELATED APPLICATIONS
[0001] The present application is a 35 U.S.C. .sctn..sctn.371
national phase conversion of PCT/EP2013/062148, filed Jun. 12,
2013, which claims priority of German Patent Application No. 10
2012 213 637.1, filed Aug. 2, 2012, the contents of which are
incorporated by reference herein. The PCT International Application
was published in the German language.
[0002] The present invention relates to a gas turbine combustion
chamber.
[0003] Combustion chambers, in particular for gas turbines, are
generally provided, internally, with a flow guiding body, called a
liner. A combustible fluid is supplied via one or more burners
provided in the combustion chamber, which fluid ignites in the
combustion space of the combustion chamber and, passing through the
liner, is guided towards the outlet opening. Since the walls of the
combustion chamber are subjected to high thermal loads due to the
combustion taking place inside the combustion chamber, these parts
of the combustion chamber have to be cooled. A thermal barrier
coating on the inside of the liner is generally not sufficient.
Cooling is achieved e.g. by means of interstices through which is
conveyed a coolant which cools the combustion chamber
convectively.
[0004] The components experience thermal expansion caused by
temperature changes which occur during operation.
[0005] The liner simultaneously represents the transition to the
turbine space and is therefore conical. The cooling system must be
able to cope with the axial and radial thermal expansion of the
liner cone and must ensure that, even in the case of changing
conditions, only a certain defined quantity of air flows along the
cone.
[0006] FIG. 1 shows a gas turbine combustion chamber with
convective cooling of the liner cone which is provided with an
external sheath.
SUMMARY OF THE INVENTION
[0007] The invention has the object of providing a gas turbine
combustion chamber with improved cooling.
[0008] A gas turbine combustion chamber has an inner wall with
cooling air bores circumferentially around it and an outer wall
around and spaced apart from the inner wall. The outer wall also
has cooling air bores. The outer wall is formed from multiple wall
elements which are arranged substantially next to one another in
the circumferential direction of the gas turbine combustion
chamber. By substantially is here meant that the wall elements can
move closer or move apart as operating temperature affects them,
but are close together enough to enable a common fastener to hold
neighboring opposing edges with a common fastener, if that is
selected. The wall elements are arranged on the inner wall by means
of a respective fixed bearing on one narrow side of each wall
element and by means of a floating bearing on an opposite narrow
side of each wall element, such that a cavity is formed between the
inner and outer walls. The outer wall cone is cooled by an
effective impingement cooling. Furthermore, the outer wall
elements, which act as impingement cooling plates, are allowed to
expand relative to the main body, i.e. the inner wall of the gas
turbine, as a consequence of different temperatures of the main
body (approx. 900-1000.degree. C.) and of the impingement cooling
plates (approx. 500-600.degree. C.)
[0009] In one advantageous embodiment, the wall elements are
arranged on the inner wall by means of a fixed bearing on the
burner side and by means of a floating bearing on the turbine
side.
[0010] It is then expedient if the inner wall is in the form of a
hollow frustum and the wall elements of the outer wall are in the
form of hollow frustum segments.
[0011] In order to better compensate for the thermal expansion in
the radial direction, adjacent outer wall elements are arranged
such that they overlap.
[0012] In one advantageous embodiment, for easier assembly the
floating bearing is comprised of ring segments each of which has a
groove for receiving in each case one narrow side of the wall
elements.
[0013] Expediently, the fixed bearing also is comprised of ring
segments.
[0014] For cooling the bearings, at least one of the bearings has
cooling air bores.
[0015] In order to prevent adjacent wall elements separating, it is
advantageous if retainers are provided in the region where the
edges of two neighboring wall elements overlap. It can then be
expedient if the retainers are attached to the inner wall.
[0016] In order to permit different thermal expansions in as
stress-free a manner as possible, also at the retainers, the wall
elements have openings for the retainers, wherein the diameters of
the openings are larger than the diameters of the retainers in this
region.
[0017] In order to prevent the wall elements of the outer wall
touching the cone of the inner wall because of thermal deformation,
spacers (pins) are arranged between the inner wall and the outer
wall. These spacers are expediently arranged, for example welded,
on the inner wall opposite a central region of the respective wall
element, i.e. in the middle beneath the wall elements.
[0018] An embodiment of the cavity formed by the inner wall and the
outer wall as an acoustic damper (resonator) is particularly
advantageous since it is thus possible to reduce the number of
resonators which would otherwise be required. On one hand, this
reduces costs and, on the other hand, it saves air which would
otherwise be required for flushing or cooling these resonators.
[0019] The advantages of the proposed solution reside in the
improved cooling of the liner cone by means of an effective
impingement cooling, and in the avoidance of the thermal stress
which results through the floating bearing. In addition, the cavity
created between the liner cone and the plates, which cavity also
acts as a resonator, damps medium- to high-frequency
vibrations.
BRIEF DESCRIPTION OF THE DRAWINGS
[0020] The invention will be explained in more detail by way of
example with reference to the drawings, which are schematic and not
to scale and in which:
[0021] FIG. 1 shows a gas turbine combustion chamber with a burner
liner according to the prior art with an external sheath for
convective cooling,
[0022] FIG. 2 shows a gas turbine combustion chamber according to
the invention with wall elements for impingement cooling,
[0023] FIG. 3 shows a wall element with cooling air bores and
openings for attachment,
[0024] FIG. 4 shows a detail of a fixed bearing ring segment,
[0025] FIG. 5 shows a section through a burner liner of a gas
turbine combustion chamber according to the invention with a fixed
bearing,
[0026] FIG. 6 shows a section through a burner liner of a gas
turbine combustion chamber according to the invention with a
floating bearing,
[0027] FIG. 7 shows a plan view of a ring segment of the floating
bearing,
[0028] FIG. 8 shows a gas turbine combustion chamber according to
the invention without wall elements,
[0029] FIG. 9 shows a bolt for retaining the wall elements and
preventing them separating,
[0030] FIG. 10 shows a bolt in the installed state with wall
elements and
[0031] FIG. 11 shows overlapping wall elements.
DESCRIPTION OF EMBODIMENTS
[0032] FIG. 1 shows, schematically and by way of example, a gas
turbine combustion chamber 1 according to the prior art with an
inner wall 2 (burner liner) which encloses the combustion space 3
and has, on the combustion space side, a thermal protection coating
4, and a sheath 5 surrounding the inner wall 2. Between the inner
wall and the sheath 5, cooling air 6 is guided for convectively
cooling the inner wall 2. In the transition from the combustion
space 3 downstream to the turbine space (not shown), the gas
turbine combustion chamber 1 and therefore also the inner wall 2 or
the burner liner 2 are conical. This region is therefore also
termed the liner cone 7.
[0033] FIG. 2 shows a gas turbine combustion chamber 8 according to
the invention with an inner wall 2 and an outer wall 9 spaced apart
therefrom, which form a cavity 10 (see FIGS. 5 and 6). The outer
wall 9 is formed by a plate construction, comprised of eight wall
elements 11, which are configured and arranged and supported to
compensate for thermal expansion of the liner cone 7. The number of
wall elements 11 can differ from that shown in the exemplary
embodiment of FIG. 2.
[0034] The wall elements 11 are welded to the inner wall 2 on that
side 12 of the liner cone 7 which is oriented towards the burner,
that is towards the base of the frustum, and are mounted in a
floating manner on that side 13 of the liner cone 7 which is
oriented towards the turbine, that is towards the top of the
frustum. However, the solution may also be reversed.
[0035] In that context, two plate rows 14, 15 are installed offset
on top of one another. For the purpose of impingement-cooling of
the inner conical wall 2 the outer wall elements 11 have cooling
air bores 16. Corresponding cooling air bores 17 are provided in
the inner wall 2 (see FIGS. 8 and 10) such that the air used for
the impingement cooling can flow into the combustion space 3.
[0036] FIG. 3 shows an outer wall element 11 with cooling air bores
16. During operation, gaps could emerge between superposed wall
elements 11, through which air could penetrate uncontrolled under
the plate construction. However, these gaps are avoided by means of
retainers 18 (see FIGS. 10-11). To that end, the wall elements 11
have openings 20 on two opposite axial sides 19. The diameter of
these openings is larger than the retainer diameter in this region
in order to guarantee, here too, sufficient play for thermal
expansion. The two other circumferential sides 21 together form,
with the ring segments 22, 23 shown in FIGS. 4 to 7, a fixed
bearing 24 and a floating bearing 25.
[0037] FIG. 4 shows a detail of a fixed bearing 24, in particular a
detail comprised of a ring segment 22 for a fixed bearing 24. If
the ring segment 22 is welded to the inner wall 2 (see FIG. 5), a
cavity 26 is formed which can be cooled via cooling air bores 27 in
the ring segment 22.
[0038] FIG. 5 shows a section through a fixed bearing 24 of a gas
turbine combustion chamber 8 according to the invention with a ring
segment 22 for the fixed bearing 24, which ring segment is arranged
on the burner liner 2 and is connected thereto at the welding
points 28, and adjacent wall elements 11 which are arranged offset
in the axial direction of the combustion chamber 8. The wall
elements 11 are connected to the ring segment 22 at the welding
points 29. For assembly reasons, adjacent wall elements 11 are
welded to the ring segments 22 offset in the axial direction.
[0039] FIG. 6 shows a section through a floating bearing 25 of a
gas turbine combustion chamber 8 according to the invention with a
ring segment 23 for the floating bearing 25, which ring segment is
arranged on the burner liner 2 and is connected thereto at the
welding points 30. The ring segment 23 of the floating bearing 25
comprises a groove 31 for receiving a narrow side 21 of the wall
elements 11 and bears directly against the inner wall 2 such that
cooling air bores in the ring segment 23 are also not
necessary.
[0040] FIG. 7 shows a ring segment 23 for the floating bearing 25.
The groove 31, for mounting the wall elements 11 in a floating
manner in the ring segment 23, runs according to the overlapping
arrangement of the wall elements 11 at various radii with
overlapping regions 32.
[0041] FIG. 8 shows a gas turbine combustion chamber 8 according to
the invention without wall elements 11. It is thus possible to see
bolts 33, as parts of the separation-preventing retainers 18, and
also other spacers or pins 34 which are arranged on the inner wall
2 and which prevent the wall elements 11 touching the cone of the
inner wall 2 because of thermal deformation. The pins 34 are
typically welded to the inner wall 2, in the middle beneath the
wall elements 11.
[0042] FIG. 9 shows a bolt 33 with a further formed element for
simpler assembly on the inner wall 2. The bolt 33 is part of a
retainer 18 as is used to prevent separation between two adjacent
wall elements 11.
[0043] FIG. 10 shows such a retainer 18 in the installed state. It
is welded to the inner wall 2 and may be arranged on the inner wall
2 in a depression 35 provided for that purpose. In the region of
the openings 21 of the wall elements 11, the diameter of the bolt
33 of the retainer 18 is smaller than that of the openings 21
themselves, such that sufficient space for thermal expansion is
present. The wall elements 11 are secured by means of a perforated
disk 36 welded thereto, such that essentially only axial
displacements of the wall elements 11 and displacements in the
circumferential direction of the gas turbine combustion chamber 8,
but no radial movements, are possible. FIG. 11 shows a plan view of
the region of the retainer 18.
[0044] Although a gas turbine combustion chamber with a conical
surrounding inner wall has been described in the exemplary
embodiments, the invention is not restricted to a conical shape.
Furthermore, the function of the device according to the invention
is not restricted to a cooling effect to be achieved, but can also
be used as a resonance absorber.
* * * * *