U.S. patent application number 10/517613 was filed with the patent office on 2005-09-15 for gas turbine ventilation circuitry.
Invention is credited to Coulon, Sylvie, Maffre, Jean-Philippe, Taillant, Jean-Claude.
Application Number | 20050201859 10/517613 |
Document ID | / |
Family ID | 29724922 |
Filed Date | 2005-09-15 |
United States Patent
Application |
20050201859 |
Kind Code |
A1 |
Coulon, Sylvie ; et
al. |
September 15, 2005 |
Gas turbine ventilation circuitry
Abstract
A ventilation circuit of a turbomachine turbine rotor having a
turbine disk and an upstream flange disposed upstream from a
combustion chamber from which it is spaced apart by a cavity. A
first cooling air circuit delivers air into the cavity via main
injectors and holes in the flange. A second cooling air circuit
delivers air through enclosures delimited by the combustion chamber
inner casing and the rotor via a discharge labyrinth, an
under-injector labyrinth, and at least one labyrinth downstream
from the main injectors between an annular structure and the
flange. Three single-wiper labyrinths delimiting two cavities
upstream from the venting cavity of the turbine disk are provided
downstream from the main injectors. One of the cavities is fed with
air from the second circuit upstream from the under-injector
labyrinth by bore holes in the annular structure sloping
tangentially in the rotation direction of the rotor.
Inventors: |
Coulon, Sylvie; (Bois Le
Roi, FR) ; Taillant, Jean-Claude; (Vaux Le Penil,
FR) ; Maffre, Jean-Philippe; (Dammarie Les Lys,
FR) |
Correspondence
Address: |
OBLON, SPIVAK, MCCLELLAND, MAIER & NEUSTADT, P.C.
1940 DUKE STREET
ALEXANDRIA
VA
22314
US
|
Family ID: |
29724922 |
Appl. No.: |
10/517613 |
Filed: |
December 22, 2004 |
PCT Filed: |
June 25, 2003 |
PCT NO: |
PCT/FR03/01958 |
Current U.S.
Class: |
415/170.1 |
Current CPC
Class: |
F01D 11/02 20130101;
Y02T 50/60 20130101; F02C 7/28 20130101; Y02T 50/676 20130101; F01D
5/081 20130101; Y02T 50/671 20130101; F01D 5/3015 20130101 |
Class at
Publication: |
415/170.1 |
International
Class: |
F01D 005/00 |
Foreign Application Data
Date |
Code |
Application Number |
Jun 27, 2002 |
FR |
02/07979 |
Claims
1-5. (canceled)
6. A turbomachine comprising: a sealing device between a turbine
rotor and an inner casing of a combustion chamber, the turbine
rotor comprising: a turbine disk presenting an upstream clamping
annulus for fastening it to a downstream cone of a compressor, and
a flange disposed upstream from the disk and spaced apart from the
disk by a cavity, the flange including an inside bore traversed by
the upstream clamping annulus of the disk and an upstream clamping
annulus so it can be fastened onto the downstream cone; a first air
circuit secured to the inner casing to deliver a first flow of
cooling into the cavity via main injectors and holes made in the
flange; the sealing device comprising a discharge labyrinth between
the downstream cone and the inner casing, a main under-injector
labyrinth disposed between the flange and an inside wall of the
first air circuit, and at least one over-injector labyrinth
disposed between the flange and an annular structure provided
between an outside wall of the first air circuit and the inner
casing, a second flow of cooling air flowing inside a second
circuit defined by enclosures delimited by the inner casing and the
rotor, by the labyrinths, and being evacuated in part in the
upstream venting cavity of the disk, wherein downstream from the
main injectors in flow direction of the second flow of cooling air,
the sealing device comprises at least three labyrinths radially
spaced apart, being disposed between the flange and the annular
structure.
7. A turbomachine according to claim 6, wherein each of the three
labyrinths comprises a single wiper.
8. A turbomachine according to claim 6, wherein one of the annular
cavities lying between two consecutive labyrinths out of the three
labyrinths is fed by cooling air coming from the second circuit
upstream from the under-injector labyrinth.
9. A turbomachine according to claim 8, wherein the flow of cooling
air is set into rotation in a same direction as rotation of the
rotor by secondary injectors.
10. A turbomachine according to claim 9, wherein the secondary
injectors are made in a form of sloping holes formed in the annular
structure.
Description
[0001] The invention relates to the field of ventilating a high
pressure turbine in an aircraft turbomachine.
[0002] More precisely, the invention relates to a turbomachine
having a sealing device between the turbine rotor and the inner
casing of the combustion chamber, said turbine rotor comprising
firstly, a turbine disk presenting an upstream clamping annulus for
fastening it to the downstream cone of a compressor and, secondly,
a flange that is disposed upstream from said disk and spaced apart
from the disk by a cavity, said flange having an inside bore that
is traversed by the upstream clamping annulus of said disk and an
upstream clamping annulus so it can be fastened onto said
downstream cone, a first air circuit secured to said inner casing
in order to deliver a first flow of cooling air into said cavity
via main injectors and holes made in said flange, said sealing
device comprising a discharge labyrinth between the downstream cone
and said inner casing, a main under-injector labyrinth disposed
between the flange and the inside wall of the first air circuit,
and at least one over-injector labyrinth disposed between the
flange and an annular structure provided between the outside wall
of the first air circuit and said inner casing, a second flow of
cooling air flowing inside a second circuit that is defined by the
enclosures that are delimited by said inner casing and said rotor,
via said labyrinths, and being evacuated in part in the venting
cavity of said disk.
[0003] FIG. 1 shows one such high pressure turbine rotor 1,
disposed downstream from a combustion chamber 2, and comprising a
turbine disk 3 fitted with blades 4, and a flange 5 disposed
upstream from the disk 3. The disk 3 and the flange 5 both include
respective upstream clamping annuluses, referenced 3a for the disk
3 and 5a for the flange 5, to enable them to be fastened to the
downstream end 6 of the downstream cone 7 of the high pressure
compressor driven by the rotor 1.
[0004] The disk 3 includes an inside bore 8 passing the shaft 9 of
a low pressure turbine, and the flange 5 presents an inside bore 10
that surrounds the clamping annulus 3a of the disk 3, and
ventilation holes 11 through which a first flow C1 of cooling air
taken from the bottom of the combustion chamber is delivered into
the cavity 12 that separates the downstream face of the flange 5
from the upstream face of the disk 3. The flow C1 of cooling air
flows radially outwards and penetrates into the recesses 4a that
contain the roots of the blades 4 in order to cool said roots. The
flow of air comes from the bottom of the combustion chamber, flows
into a duct 13 disposed inside the enclosure 14 that separates the
flange 5 from the bottom of the combustion chamber, and is drawn
into rotation by injectors 15 in order to lower the temperature of
the air delivered into the cavity 12.
[0005] A second flow C2 of cooling air taken from the bottom of the
combustion chamber flows downstream inside the enclosure 16 that
separates the downstream cone 7 in the high pressure compressor
from the inner casing 17 of the combustion chamber 2. The flow C2
of air flows through a discharge labyrinth 18 and penetrates into
the enclosure 14 from whence one portion C2a flows through the
orifices 19 made in the upstream clamping annulus 5a of the flange
5, and then passes through the bore 10 of the flange 5 in order to
cool the radially inner portion of the flange and joins flow C1 of
air cooling the blades 4. Another portion C2b of the second flow C2
of air cools the upstream face of the flange 5, flows around the
injectors 15 and is evacuated into the upstream venting cavity 20
of the turbine rotor 1.
[0006] Lastly, a third portion C2c of the second flow C2 of air
serves to ventilate the upstream top face 21 of the flange 5
through a second labyrinth 22 that is situated under the injectors
15. The third portion C2c penetrates into the enclosure 23 that is
situated downstream of the second labyrinth 22, between the flange
5 and the injectors 15, and is evacuated into the upstream venting
cavity of the turbine rotor 1 through a third labyrinth 24 that is
situated above the injectors 15, or else it is mixed with the first
flow C1 of air.
[0007] The second flow C2 of air serves to cool the downstream cone
7, the connection drum connecting the high pressure compressor to
the high pressure turbine, and the flange 5. The second air flow
that flows axially in an annular space delimited by the stationary
walls secured to the chamber and the adjustable rotating walls
secured to the rotor is heated by the power dissipated between the
rotor and the stator.
[0008] In order to lower the temperature of the upstream flange to
comply with its mechanical behavior specifications, it is therefore
necessary to increase the flow C2 of air going through the
discharge labyrinth 18 that is situated downstream from the high
pressure compressor, and to expel it either into the circuit for
cooling the blades or else into the exhaust gas stream that is
upstream from the high pressure turbine wheel. Such an increase of
flow rate results in an increase in the temperature of the air that
cools the blades due to the discharge of air that has been heated
in the blade cooling circuit, and results in a drop in performance
of the turbine due to the discharge into the exhaust gas
stream.
[0009] Moreover, the flow C2c of air that serves to cool the flange
downstream from the second labyrinth 22, said labyrinth being
situated under the injectors 15, cannot be easily controlled since
it is subject to the variations that occur, while the engine is in
operation and over the lifetime of said engine, in the clearances
in the discharge labyrinth 18, in the second labyrinth 22, and in
the third labyrinth 24, said third labyrinth being situated above
the injectors 15.
[0010] In order to prevent large leaks from passing through the
third labyrinth 24 that is situated above the injectors 15, said
third labyrinth comprises three successive wipers that are formed
on an angled portion 25 of the flange 5, said wipers cooperating
with sealing elements 26 secured to an annular structure 27
inserted between the outside wall 28 of the duct 13 and the
upstream portion 29 of the inside casing 27. This type of
three-wiper labyrinth is of a considerable weight, and, because of
centrifugal forces, it requires the flange 5 to be fastened onto
the upstream face of the turbine disk 3 by means of a claw coupling
30.
[0011] The prior art is also described in FR 2 541 371 and FR 2 744
761. Both documents teach the presence of two labyrinths downstream
from the main injectors, and the first flow of air crossing through
the second flow of air via branch ducts passing through the circuit
for the first flow of air.
[0012] The first object of the invention is to modify the sealing
device upstream from the main injectors, in order to lighten the
upstream flange.
[0013] A second object of the invention is to allow for a decrease
in the venting flow rate upstream from the rotor, thereby achieving
a saving in specific consumption.
[0014] A third object of the invention is to raise the pressure
levels in the cooling air supply circuit of the turbine wheel,
which is favorable for cooling the blades.
[0015] The invention achieves the first object by the fact that,
downstream from the main injectors in the flow direction of the
second flow of cooling air, the sealing device comprises at least
three labyrinths that are radially spaced apart, being disposed
between the flange and the annular structure.
[0016] Most advantageously, each of said three labyrinths comprises
a single wiper.
[0017] Each of the labyrinths is thus light in structure, which
makes it possible to omit the claw coupling.
[0018] The invention achieves the second and third objects by the
fact that one of the annular cavities lying between two consecutive
labyrinths out of said three labyrinths is fed by cooling air
coming from the second circuit upstream from the under-injector
labyrinth.
[0019] Advantageously, this third flow of air is drawn into
rotation in the same direction as the rotation of the rotor by the
secondary injectors.
[0020] Preferably, the secondary injectors are made in the form of
sloping holes formed in the annular structure.
[0021] Other advantages and characteristics of the invention appear
on reading the following description given by way of example and
with reference to the accompanying drawings in which:
[0022] FIG. 1 is an axial half-section of a high pressure turbine
rotor in a turbojet, showing the cooling air circuits and the
different sealing labyrinths of the prior art; and
[0023] FIG. 2 is an axial half-section of a turbojet turbine rotor
showing the disposition of the flange and the labyrinths of the
invention, upstream from the main injectors.
[0024] The prior art shown in FIG. 1 is described in the
introduction and needs no further explanation.
[0025] FIG. 2 shows a high pressure turbine rotor referenced 1 that
is disposed downstream from a combustion chamber 2, which comprises
a turbine disk 3 fitted with blades 4 on its periphery, and a
flange 5 that is disposed upstream from the disk 3. The disk 3 and
the flange 5 define between them a cavity 12 that is fed with
cooling air via main injectors 15 and via holes 11 made in the
flange 5 and opposite the main injectors 15. The main injectors 15
slope relative to the axis of rotation of the turbine so as to
direct the air they supply in the direction of rotation of the
turbine rotor 1.
[0026] The main injectors 15 are fed with air taken from the bottom
of the combustion chamber by means of an annular duct 13 which
comprises a radially inner wall 13a and a radially outer wall
28.
[0027] A second labyrinth, not shown in FIG. 2, is disposed under
the main injectors, between the radially inner wall 13a and the
flange 5. An annular structure 27 is inserted between the radially
outer wall 28 of the duct 13 and the upstream portion 29 of the
inner casing of the combustion chamber 2.
[0028] As can be seen in FIG. 2, the invention provides for three
radially spaced apart labyrinths 31, 32, and 33, replacing the
third labyrinth 24 of the prior art, said three labyrinths lying
between the cavity 23 that is situated upstream from the second
labyrinth and the upstream venting cavity 20 in the turbine rotor 1
and above the main injectors 15. Each of the three labyrinths 31,
32, and 33 comprises a single wiper, and together they define two
intermediate cavities 34 and 35 between the enclosure 23, into
which the main injectors 15 and the upstream venting cavity 2
emerge.
[0029] Without leaving the ambit of the invention, the labyrinths
31, 32, and 33 could be replaced by other rotor/stator sealing
systems, such as brush gaskets, and there could also be a
combination of labyrinths and of brush gaskets.
[0030] Branch holes 36 made through the wall of the annular duct 13
serve to put the enclosure 14, which is under the combustion
chamber and is disposed downstream from the second labyrinth that
is situated under the main injectors, into communication with the
enclosure 37 that is situated radially outer the annular duct 13.
Bore holes 38 that slope relative to the axis of rotation of the
turbine rotor 1 are made in the annular structure 27 between the
enclosure 37 and the cavity 35 that is situated immediately
upstream from the venting cavity 20. The bore holes 38 slope in the
direction of rotation of the turbine rotor 1 in order to reduce the
temperature of the cooling air of the radially outer wall of the
flange 5.
[0031] Because the air penetrating into the cavity 35 through the
bore holes 38 comes from upstream from the labyrinth under the
injectors, pressure in the cavity 35 is increased and the amount of
air escaping through the labyrinths 31 and 32 is decreased.
[0032] This leads to increased pressure in the cavities 23 and 12,
which is favorable to cooling the blades 4.
[0033] The fact that the invention replaces one over-injector
labyrinth 24 of the prior art, comprising three wipers, with three
radially spaced apart labyrinths 31, 32 and 33, each having a
single wiper, makes it possible to simplify the structure of the
radially outer portion of the flange 5. This portion comes in the
form of a web having a radially inner end bearing on the roots of
the blades 4 and on the teeth of the disk. Such a disposition makes
it possible to reduce the weight of the flange 5 and eliminates the
claw coupling of the flange 5 onto the disk 3, which increases the
life times of the flange 5 and of the disk 3.
[0034] The bore holes 38 are graded in order to reduce the amount
of air escaping from the venting cavity 20, which makes it possible
to reduce specific consumption by about 0.1%.
[0035] The bore holes 38 constitute a system of secondary injectors
which make it possible, via the branch holes 36 to make use of most
of the air in the under-chamber cavity to cool the top of the
upstream flange. This flow of air meets the air that cools the
blades, which is why it is commonly referred to as a "shunt" flow.
Without leaving the ambit of the invention, the sloping bore holes
38 may be replaced with vaned injectors or with sloping tubes,
assembled in the wall of the annular structure 27.
* * * * *