Power plants – Combustion products used as motive fluid – Combustion products generator
Reexamination Certificate
2002-04-03
2004-05-11
Kim, Ted (Department: 3746)
Power plants
Combustion products used as motive fluid
Combustion products generator
C060S746000, C060S757000
Reexamination Certificate
active
06732528
ABSTRACT:
FIELD OF THE INVENTION
The present invention relates to a gas turbine combustor which can effectively suppress burning loss generated on the internal wall surface of a tail cylinder due to the catching of combustion gas.
BACKGROUND OF THE INVENTION
In a gas turbine combustor, there has been conventionally employed a structure which has an opening section of an internal cylinder inserted into a tail cylinder and installed there.
FIG. 11
is a cross section of a complete conventional gas turbine combustor.
FIG. 12
is an enlarged cross-sectional diagram and
FIG. 13
is a front diagram of required portions of the gas turbine combustor shown in FIG.
11
. As shown in
FIG. 11
to
FIG. 13
, a gas turbine combustor
100
is constructed of an external cylinder
111
which is installed on a vehicle chamber
110
, a tail cylinder
120
which is disposed within the vehicle chamber
110
, an internal cylinder
130
which is inserted into and installed on this tail cylinder
120
, and an external cylinder casing
112
which positions and fixes the internal cylinder
130
relative to the external cylinder
111
. The external cylinder
111
is prepared using a metal member having a circular cylinder section, and is installed on the external side of the vehicle chamber
110
, with the circular cylinder section set substantially perpendicular to this external side. The external cylinder
111
is fixed to the vehicle chamber
110
with bolts not shown. The tail cylinder
120
is prepared using a thin metal member, and has a circular cylinder section
121
and a nozzle section, not shown, with a front end of the circular cylinder section
121
curved mildly. The tail cylinder
120
is fixed, with a front end of the nozzle section connected to a combustion path of a turbine not shown. The tail cylinder
120
is installed on the external cylinder
111
, with the circular cylinder section
121
inserted into the external cylinder
111
. The tail cylinder
120
is positioned substantially on the same axis with the external cylinder
111
.
The internal cylinder
130
is prepared using a metal member having a circular cylindrical shape. An opening section
131
of the internal cylinder
130
expands mildly and reaches an internal wall surface
122
of the tail cylinder
120
. The internal cylinder
130
has a spring plate
132
made of a metal member, and a sealing plate
133
which is supported with this spring plate
132
, on a side wall in the vicinity of the opening section
131
. Further, the internal cylinder
130
has a pilot nozzle
140
which jets diffusion flame, and eight main nozzles
141
which are disposed around the pilot nozzle
140
and which jets combustion gas, within the internal cylinder
130
. This pilot nozzle
140
has a tubular pilot cone
142
at its front end, and has a pilot fuel jet nozzle
143
inside the tubular pilot cone
142
. The main nozzle
141
is extended with a main nozzle extension cylinder
144
in the vicinity of the opening section
131
of the internal cylinder
130
, and has a jet section
145
at substantially the same position as the pilot cone
142
. A main fuel jet nozzle
145
is disposed inside the main nozzle
141
. The pilot nozzle
140
and the main nozzle
141
are fixed to the internal cylinder
130
with a substrate
147
which is installed on the internal wall of the internal cylinder
130
.
The internal cylinder
130
is installed on the tail cylinder
120
, with the opening section
131
inserted into the tail cylinder
120
. The sealing plate
133
of the internal cylinder
130
is biased toward the internal wall of the tail cylinder
120
with the spring plate
132
, and seals a section of engagement between the tail cylinder
120
and the internal cylinder
130
. The internal cylinder
130
is engaged with the tail cylinder
120
by pressing the sealing plate
133
against the tail cylinder. An entrance
134
of the internal cylinder
130
is supported with the external cylinder casing
112
, and the internal cylinder
130
is positioned substantially on the same axis with the external cylinder
111
. The internal cylinder
130
is fixed to an aligned position, by having the external cylinder casing
112
fixed to the external cylinder
111
with bolts not shown. The internal cylinder
130
has a stay
135
which takes compressed air
150
into the inside, at the entrance
134
. A reference numeral
113
denotes a pilot fuel supply opening
113
from which fuel is supplied to the pilot fuel jet nozzle
143
, and reference numeral
114
denotes a main fuel supply opening
114
from which fuel is supplied to the main fuel jet nozzle
146
.
In the conventional gas turbine combustor
100
, air
150
compressed with a compressor not shown passes through a flow path
115
which is encircled with the external peripheral surface of the tail cylinder
120
and the external peripheral surface of the internal cylinder
130
, and the internal peripheral surface of the external cylinder
111
. This air enters the internal cylinder
130
from the stay
135
. Air
151
which has entered the internal cylinder
130
is mixed with main fuel within the main nozzle
141
, and a mixed gas is formed. This pre-mixed air
152
is blown out from the main nozzle extension cylinder
148
, and is ignited with the diffusion flame, not shown, which is emitted from the pilot nozzle
140
, to form a high-temperature combustion gas
153
. This combustion gas
153
is blown out into the tail cylinder
120
from the opening section
131
of the internal cylinder
130
, and is combusted within a combustion chamber
125
, and the combusted gas is supplied to the turbine.
According to the conventional gas turbine combustor
100
, however, there has been a problem that the internal wall of the tail cylinder
120
is damaged by burning with the combustion gas
153
which is blown out from the opening section
131
of the internal cylinder
130
. In other words, according to the gas turbine combustor
100
having such a structure that the opening section
131
of the internal cylinder
130
is inserted into and engaged with the tail cylinder
120
, the edge of the opening section
131
and the internal wall surface
122
of the tail cylinder
120
are not smoothly connected to each other. Therefore, a gap
124
generated at this connection section catches the high-temperature combustion gas
153
which has been blown out from the opening section
131
, and this combustion gas burns the internal wall surface
122
of the tail cylinder
120
.
SUMMARY OF THE INVENTION
The present invention has been achieved in order to solve the above problems and it is an object of this invention to provide a gas turbine combustor which can effectively suppress burning loss generated on the internal wall surface of the tail cylinder in the vicinity of the opening section of the internal cylinder.
In the gas turbine combustor according to the present invention, compressed air is jetted along an internal wall surface of a tail cylinder from a clearance secured between the internal wall surface of the tail cylinder and an edge of an opening section of an internal cylinder. As a result, a film of cooling air is formed on the internal wall surface of the tail cylinder whereby the internal wall surface of the tail cylinder is protected from a high-temperature combustion gas which is blown out from the opening section of the internal cylinder.
Other objects and features of this invention will become apparent from the following description with reference to the accompanying drawings.
REFERENCES:
patent: 2664702 (1954-01-01), Lloyd et al.
patent: 2860483 (1958-11-01), Fox
patent: 3705492 (1972-12-01), Vickers
patent: 4392355 (1983-07-01), Verdouw
patent: 5239831 (1993-08-01), Kuroda et al.
patent: 5357745 (1994-10-01), Probert
patent: 5479772 (1996-01-01), Halila
patent: 5487275 (1996-01-01), Borkowicz et al.
patent: 5836164 (1998-11-01), Tsukahara et al.
patent: 5950417 (1999-09-01), Robertson et al.
patent: 6056538 (2000-05-01), Buchner et al.
patent: 6082111 (2000-07-01), Stokes
patent: 6105372
Akagi Kouichi
Tomimoto Souichirou
Kim Ted
Mitsubishi Heavy Industries Ltd.
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