CN104675454B - A kind of gas turbine combustion cylinder pressure heat insulation structural - Google Patents
A kind of gas turbine combustion cylinder pressure heat insulation structural Download PDFInfo
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- CN104675454B CN104675454B CN201510050842.2A CN201510050842A CN104675454B CN 104675454 B CN104675454 B CN 104675454B CN 201510050842 A CN201510050842 A CN 201510050842A CN 104675454 B CN104675454 B CN 104675454B
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- cylinder pressure
- combustion cylinder
- instlated tubular
- gas turbine
- heat insulation
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Abstract
The present invention relates to gas turbine fields, disclose a kind of gas turbine combustion cylinder pressure heat insulation structural, the combustion cylinder pressure includes outer shell and inner casing, the inner casing and outer shell collectively form the chamber of combustion cylinder pressure, multiple supports of connection outer shell and inner casing are equipped in the chamber, the bleed hole for being connected to the outer shell and inner casing is equipped at least one described support, instlated tubular is equipped in the bleed hole, the inlet end of the instlated tubular and the air inlet in the bleed hole are cooperatively connected, and there are gaps between the pipe shaft of the instlated tubular and the bleed hole.The present invention can be effectively isolated the heat exchange between the cold air in bleed hole and combustion cylinder pressure chamber, avoid the generation of thermal stress；And it can be avoided and generate excessive thermal stress between instlated tubular and support.
Description
Technical field
The present invention relates to technical field of gas turbine, more particularly to a kind of gas turbine combustion cylinder pressure heat insulation structural.
Background technique
The continuous innovation and development of modern gas turbines technology, for the whole thermal efficiency for improving combustion engine, turbine inlet temperature is not
It is disconnected to increase.Turbine rotor blade works at the same time under high temperature environment as high-speed rotary part, only relies on materials'use temperature
The raising of degree can no longer meet actual use demand, and turbine rotor blade must take the cooling of certain forms.Turbine rotor blade, it is cold
But gas is generally from compressor pumping, requires higher and higher with cooling, sucking rate demand is also increasing, will lead to combustion gas wheel
The decline of the machine thermal efficiency.
Therefore a kind of ideal method is that the air extracted out from compressor 1 will calm the anger by intercooler 4
The temperature that machine 1 is evacuated further decreases, and to reduce the flow of pumping, increases the efficiency of cycle of complete machine.But use this scheme
It being cooled down, an inevitable problem is exactly how to be evacuated compressor 1 after cooling, be reintroduced back to internal rotor, with
Just turbine rotor blade 7 is cooled down.Existing scheme as shown in Figure 1, by combustion cylinder pressure inner casing 9, outer shell 8 design be structure as a whole, inside and outside cylinder it
Between be attached using several supports 10, venthole 11 is machined in support 10, cooling air is entered by venthole 11 to be turned
It is cooled down inside son 13.
Since the air in venthole 11 is after the cooling of subcooler 4, temperature has been substantially reduced, for support 10
Speech, inside are connected with the cooling air of low temperature, external then surrounded by high-temperature gas in the chamber of combustion cylinder pressure 35, will cause support 10 greatly
Thermal stress, excessive thermal stress will lead to support 10 and cracks and damage.
Summary of the invention
(1) technical problems to be solved
The invention solves the first technical problem be the cold air how being effectively isolated in bleed hole and combustion cylinder pressure chamber
Between heat exchange, avoid the generation of thermal stress；
The second technical problem to be solved is how to avoid generating excessive thermal stress between instlated tubular and support.
(2) technical solution
In order to solve the above technical problem, the present invention provides a kind of gas turbine combustion cylinder pressure heat insulation structural, the combustion cylinder pressures
Including outer shell and inner casing, the inner casing and outer shell collectively form the chamber of combustion cylinder pressure, and connection outer shell and interior is equipped in the chamber
Multiple supports of cylinder, at least one described support is interior to be equipped with the bleed hole for being connected to the outer shell and inner casing, the bleed Kong Zhongshe
There are instlated tubular, the air inlet mating connection of the inlet end of the instlated tubular and the bleed hole, the pipe shaft of the instlated tubular and institute
State between bleed hole that there are gaps.
Wherein, the inlet end of the instlated tubular is equipped with annular convex platform, and the inlet end of the instlated tubular passes through the convex annular
Platform and the air inlet in the bleed hole are cooperatively connected.
Wherein, the top of the inlet end of the instlated tubular is equipped with flange.
Wherein, the combustion cylinder pressure is equipped with snorkel and cooler, the both ends of the cooler by the snorkel with
The inlet end of the outer shell connection, the outlet side of the snorkel and the instlated tubular passes through flanged joint.
Wherein, the pipe shaft of the instlated tubular is equipped at intervals with one or more annular convex platform along its length.
Wherein, the outer surface of the one or more annular convex platform on the instlated tubular pipe shaft is arc-shaped.
Preferably, the outer surface of the instlated tubular is enclosed with heat-barrier material.
Wherein, the instlated tubular is made of stainless steel.
(3) beneficial effect
Compared with prior art, the invention has the following advantages that
A kind of gas turbine combustion cylinder pressure heat insulation structural provided by the invention can be with using instlated tubular is equipped in bleed hole
The heat exchange between cold air and combustion cylinder pressure chamber in effective isolation bleed hole, to avoid the generation of thermal stress；And using institute
The air inlet of the inlet end and the bleed hole of stating instlated tubular is cooperatively connected, between the pipe shaft of the instlated tubular and the bleed hole
There are gap so that instlated tubular can Free Transform, and then avoid generating excessive heat between the instlated tubular and support
Stress.
Detailed description of the invention
Fig. 1 is the overall structure diagram of prior art combustion cylinder pressure；
Fig. 2 is a kind of overall structure diagram of gas turbine combustion cylinder pressure heat insulation structural of the present invention；
Fig. 3 is the instlated tubular structure of the embodiment of the present invention one；
Fig. 4 is the instlated tubular structure of the embodiment of the present invention two；
Fig. 5 is the instlated tubular structure of the embodiment of the present invention three.
In figure: 1: compressor；2: combustion chamber；3: combustion cylinder pressure 3；4: cooler 4；5: chamber；6: turning quiet disk chamber；7: turbine is dynamic
Leaf；8: outer shell；9: inner casing；10: support；11: bleed hole；12: snorkel；13: rotor；14: instlated tubular；14a: flange；14b:
Annular convex platform；14c: instlated tubular pipe shaft.
Specific embodiment
With reference to the accompanying drawings and examples, specific embodiments of the present invention will be described in further detail.Following instance
For illustrating the present invention, but it is not intended to limit the scope of the invention.
In the description of the present invention, it should be noted that term " center ", " longitudinal direction ", " transverse direction ", "upper", "lower",
The orientation or positional relationship of the instructions such as "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom" "inner", "outside" is
It is based on the orientation or positional relationship shown in the drawings, is merely for convenience of description of the present invention and simplification of the description, rather than instruction or dark
Show that signified device or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as pair
Limitation of the invention.
In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, term " installation ", " phase
Even ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or be integrally connected；It can
To be mechanical connection, it is also possible to be electrically connected；It can be directly connected, can also can be indirectly connected through an intermediary
Connection inside two elements.For the ordinary skill in the art, above-mentioned term can be understood at this with concrete condition
Concrete meaning in invention.
In addition, in the description of the present invention, unless otherwise indicated, " multiple ", " more ", " multiple groups " be meant that two or
It is more than two.
Embodiment one
As shown in Fig. 2, being a kind of 3 heat insulation structural of gas turbine combustion cylinder pressure provided by the invention, the combustion cylinder pressure 3 includes outer
Cylinder 8 and inner casing 9, the inner casing 9 and outer shell 8 collectively form the chamber 5 of combustion cylinder pressure 3, and connection 8 He of outer shell is equipped in the chamber 5
The inner casing 9 and outer shell 8 are connected as an entirety by the support 10, gone back in the chamber 5 by multiple supports 10 of inner casing 9
Equipped with combustion chamber 2, multiple supports 10 are evenly arranged on the circumferential direction of the combustion chamber 2；The company of being equipped at least one described support 10
Lead to the bleed hole 11 of the outer shell 8 and inner casing 9, is equipped with instlated tubular 14 in the bleed hole 11, bleed hole can effectively be isolated
Heat exchange between 3 chamber of cold air in 11 and combustion cylinder pressure, to avoid the generation of thermal stress；The inlet end of the instlated tubular 14 with
The air inlet in the bleed hole 11 is cooperatively connected, and there are gaps between the pipe shaft of the instlated tubular 14 and the bleed hole 11；Cause
This expanded by heating or by cold events when the instlated tubular 14 can Free Transform, and then avoid the instlated tubular 14 and support
Excessive thermal stress is generated between 10.
It is reliably connected in order to facilitate instlated tubular 14 and bleed hole 11, as shown in figure 3, the inlet end of the instlated tubular 14 is equipped with
The inlet end of annular convex platform 14b, the instlated tubular 14 are cooperated by the annular convex platform 14b and the air inlet in the bleed hole 11
Connection, convenient for positioning；1 exit gas of compressor enters cooler 4, passes through after cooling and enters instlated tubular 14 by snorkel 12, imports
Turn quiet disk chamber 6, is cooled down into turbine.
In order to facilitate the installation of, the top of the inlet end of the instlated tubular 14 is equipped with flange 14a；The combustion cylinder pressure 3 is equipped with
The both ends of snorkel 12 and cooler 4, the cooler 4 are connected to by the snorkel 12 with the outer shell, the snorkel
12 outlet side is connect with the inlet end of the instlated tubular 14 by flange 14a.
Preferably, the instlated tubular 14 is that stainless steel is made such as Cr18Ni9, the outer surface of the instlated tubular 14 be enclosed with every
Hot material, it is thermally conductive to further decrease.
Embodiment two
Embodiment two the difference is that only with embodiment one, as shown in figure 4, the instlated tubular pipe shaft 14c is along its length
Degree direction is also equipped at intervals with one or more annular convex platform 14b, prevents longer instlated tubular 14 from generating vibration and fatigue disconnected
It splits.
Embodiment three
Embodiment three the difference is that only with embodiment one, as shown in figure 5, being located on the instlated tubular pipe shaft 14c
The outer surface of the one or more annular convex platform 14b be arc-shaped, to further decrease heat transfer.
As can be seen from the above embodiments, the present invention can effectively be isolated cold air in bleed hole 11 and combustion cylinder pressure 3 it
Between heat exchange, avoid the generation of thermal stress；Meanwhile instlated tubular 14 is also equipped with the ability of Free Transform, to avoid 14 He of instlated tubular
Excessive thermal stress is generated between support 10.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all in essence of the invention
Within mind and principle, any modification, equivalent replacement, improvement and so on be should all be included in the protection scope of the present invention.
Claims (8)
1. a kind of gas turbine combustion cylinder pressure heat insulation structural, the combustion cylinder pressure includes outer shell and inner casing, and the inner casing and outer shell are common
The chamber of combustion cylinder pressure is constituted, multiple supports of connection outer shell and inner casing are equipped in the chamber, are set at least one described support
Have the bleed hole for being connected to the outer shell and inner casing, which is characterized in that in the bleed hole be equipped with instlated tubular, the instlated tubular into
The air inlet in gas end and the bleed hole is cooperatively connected, and there are gaps between the pipe shaft of the instlated tubular and the bleed hole.
2. gas turbine combustion cylinder pressure heat insulation structural as described in claim 1, which is characterized in that the inlet end of the instlated tubular is set
There is annular convex platform, the inlet end of the instlated tubular is cooperatively connected by the annular convex platform and the air inlet in the bleed hole.
3. gas turbine combustion cylinder pressure heat insulation structural as described in claim 1, which is characterized in that the inlet end of the instlated tubular
Top is equipped with flange.
4. gas turbine combustion cylinder pressure heat insulation structural as claimed in claim 3, which is characterized in that the combustion cylinder pressure is equipped with ventilation
Pipe and cooler, the both ends of the cooler are connected to by the snorkel with the outer shell, the outlet side of the snorkel and
The inlet end of the instlated tubular passes through flanged joint.
5. gas turbine combustion cylinder pressure heat insulation structural as claimed in claim 2, which is characterized in that the pipe shaft of the instlated tubular is along it
Length direction is equipped at intervals with one or more annular convex platform.
6. gas turbine combustion cylinder pressure heat insulation structural as claimed in claim 5, which is characterized in that be located on the instlated tubular pipe shaft
The outer surfaces of the one or more annular convex platform be arc-shaped.
7. gas turbine combustion cylinder pressure heat insulation structural as claimed in any one of claims 1 to 6, which is characterized in that the instlated tubular
Outer surface is enclosed with heat-barrier material.
8. gas turbine combustion cylinder pressure heat insulation structural as described in claim 1, which is characterized in that the instlated tubular is stainless steel
At.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510050842.2A CN104675454B (en) | 2015-01-30 | 2015-01-30 | A kind of gas turbine combustion cylinder pressure heat insulation structural |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510050842.2A CN104675454B (en) | 2015-01-30 | 2015-01-30 | A kind of gas turbine combustion cylinder pressure heat insulation structural |
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| Publication Number | Publication Date |
|---|---|
| CN104675454A CN104675454A (en) | 2015-06-03 |
| CN104675454B true CN104675454B (en) | 2019-10-01 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510050842.2A Active CN104675454B (en) | 2015-01-30 | 2015-01-30 | A kind of gas turbine combustion cylinder pressure heat insulation structural |
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201874655U (en) * | 2010-11-17 | 2011-06-22 | 谭大成 | Exhaust pipe for motorcycle engines |
| CN204591376U (en) * | 2015-01-30 | 2015-08-26 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of gas turbine combustion cylinder pressure heat-insulating structure |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH09151751A (en) * | 1995-11-29 | 1997-06-10 | Mitsubishi Heavy Ind Ltd | Gas turbine inner shaft seal device |
-
2015
- 2015-01-30 CN CN201510050842.2A patent/CN104675454B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201874655U (en) * | 2010-11-17 | 2011-06-22 | 谭大成 | Exhaust pipe for motorcycle engines |
| CN204591376U (en) * | 2015-01-30 | 2015-08-26 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of gas turbine combustion cylinder pressure heat-insulating structure |
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| Publication number | Publication date |
|---|---|
| CN104675454A (en) | 2015-06-03 |
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