CN107559091A - A kind of gas turbine - Google Patents
A kind of gas turbine Download PDFInfo
- Publication number
- CN107559091A CN107559091A CN201710750436.6A CN201710750436A CN107559091A CN 107559091 A CN107559091 A CN 107559091A CN 201710750436 A CN201710750436 A CN 201710750436A CN 107559091 A CN107559091 A CN 107559091A
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- barrel cover
- turbine
- protection
- rotating shaft
- impeller
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Abstract
The present invention relates to technical field of power equipment, especially a kind of gas turbine.It include compressor, combustion chamber, turbine and cooling device and front end the air intake of compressor is assemblied in by clutch shaft bearing, rear end be assemblied in by second bearing turbine exhaust end central rotating shaft；Cooling device includes protecting barrel cover in outer barrel cover and protection, air guide barrel cover is distributed between barrel cover in the outer barrel cover of protection and protection, support column is provided with air guide barrel cover, protects on the perisporium of outer barrel cover and offers cold air main-inlet, formed with waste gas passing away between adjacent two air guide barrel covers.The characteristics of present invention utilizes pressure difference and the temperature difference, the suction of cooling air can be completed while body discharges high-temp waste gas, so as to not interfere with the exhaust efficiency (or operating efficiency) of body not only, and the cooling effect to parts such as the second bearing of the exhaust end of body and support columns can be reached, it can effectively avoid above-mentioned part from being chronically in hot environment, improve body service life and the stability of work.
Description
Technical field
The present invention relates to technical field of power equipment, especially a kind of gas turbine.
Background technology
Gas turbine, which is a kind of, to be rotated at a high speed as working medium impeller using the gas continuously flowed and turns the energy of fuel
It is changed into the internal combustion type dynamic power machine of useful work；Its mainly by compressor (i.e.：Compressor), the three big portions such as combustion chamber and gas turbine
Part forms, wherein, compressor continuously sucks air and compressed it from air；Air after compression enters combustion chamber, with
The fuel mixing after-combustion of penetrating, turns into high-temperature fuel gas, immediately flow into gas turbine in expansion work, promote turbine wheel with
Compressor impeller rotates together；The acting ability of high-temperature fuel gas after heating significantly improves, thus, gas turbine is in band action pneumatic
While machine, still there is output mechanical work of the complementary work as gas turbine.Because of small volume, in light weight, startup specific to it soon, less
With or without series of advantages such as cooling waters in the field extensive use such as generating, aviation, ship.
Under normal circumstances, exhaust apparatus can be set in the end side of the gas turbine of gas turbine, and exhaust apparatus
It is typically provided in housing for carrying out the diffuser of effective ground pressure recovery to the high-temperature gas discharged by gas turbine, can revolve
Turn ground and support the rotor bearing of whole body and for realizing the parts such as the pillar of mutual supporting role between part.Mesh
Before, higher requirement is proposed to the efficiency of gas turbine, and then also cause the temperature of its waste gas also to increase, due to diffusion
The parts such as device, bearing, pillar can be chronically in the exhaust environment of high temperature, it is easy to caused part to be damaged, and then triggered combustion gas
Turbine integrally breaks down.
Therefore, it is necessary to improvement project is proposed to existing gas turbine, to appropriate cold by being carried out to above-mentioned parts
But the overall performance of gas turbine is ensured.
The content of the invention
For above-mentioned the shortcomings of the prior art, it is an object of the invention to provide a kind of gas turbine.
To achieve these goals, the present invention adopts the following technical scheme that：
A kind of gas turbine, it includes order and is distributed and is connected the compressor being integrated, combustion chamber and turbine and passes through
The central rotating shaft of compressor, combustion chamber and turbine distribution is through at, the front end of the central rotating shaft is assemblied in by clutch shaft bearing
The air intake of compressor, rear end are assemblied in the exhaust end of turbine by second bearing, and it also includes a cooling device；
The cooling device docks the outer barrel cover of the protection being integrated with the exhaust end port of turbine including one and one put
In protecting in outer barrel cover and be in barrel cover in the protection being coaxially distributed with protecting outer barrel cover, the outer barrel cover of the protection and barrel cover in protecting
Between and along second bearing radial direction ring it is all several be distributed with pass through the sky in protection between barrel cover and second bearing
Between the air guide barrel cover that is connected with the exhaust end port of turbine, be provided with one in each air guide barrel cover and be used for second
With protecting the support column that the internal perisporium of outer barrel cover is connected as a single entity, the protection on the perisporium of barrel cover and is located at the periphery wall of bearing outside
At least one cold air main-inlet is offered in the profile of each air guide barrel cover, between adjacent two air guide barrel covers
Formed with waste gas passing away, the waste gas passing away is connected with the exhaust end port of turbine.
Preferably, the outer barrel cover of the protection includes outer on the outer circumferential side for the exhaust port that a front port butts up against turbine
The outer barrel cover of layer and one be placed in the outer barrel cover of outer layer and protect between barrel cover and front port butts up against the interior of the exhaust port of turbine
The outer barrel cover of internal layer in the week side of boss, formed between barrel cover and the outer barrel cover of outer layer and positioned at the rear end side of cold air main-inlet in the internal layer
There are several and the one-to-one additional-air inlet chamber of air guide barrel cover, the air guide barrel cover is arranged at barrel cover and protection inner cylinder in internal layer
It is connected between cover and by additional-air inlet chamber with the space in protection between barrel cover and second bearing, the support column is by outside outer layer
The internal perisporium of barrel cover and the periphery wall of second bearing are connected as a single entity；On the perisporium of the outer barrel cover of the outer layer and it is located at each cold air master
The rear end side of entrance is further opened with least one auxiliary entrance of the cold air being connected with additional-air inlet chamber.
Preferably, formed with a U-shaped annular groove on the periphery wall of the outer barrel cover of the outer layer, the cold air main-inlet is positioned at U-shaped
In annular groove, the vertical range between the cold air main-inlet and central rotating shaft is less than hanging down between the auxiliary entrance of cold air and central rotating shaft
Straight distance.
Preferably, one is provided with along outside outer layer on the internal perisporium of the outer barrel cover of the outer layer and positioned at the rear end side of U-shaped annular groove
The axial directional distribution of barrel cover and the spoiler for being located at additional-air inlet intracavitary.
Preferably, the additional-air inlet intracavitary and several are additionally provided between barrel cover and spoiler along outer positioned at outer layer is outer
The axial direction distribution of the outer barrel cover of layer and the flow distribution plate being distributed each other along the circumferential direction uniform intervals of barrel cover outside outer layer.
Preferably, barrel cover is back-end closure, the tubular structure body of front opening in the protection.
Preferably, the compressor include a front end by the front end of clutch shaft bearing and central rotating shaft assembling be integrated, after
End is connected the compressor casing being integrated with combustion chamber, that several are placed in compressor casing is interior and enter under the drive of central rotating shaft
Calm the anger active impeller and several fixed impellers of calming the anger being placed in compressor casing that row rotates, the fixed impeller of calming the anger
Fore-and-aft direction of the active impeller along central rotating shaft is distributed in interleaved with calming the anger, and the diameter and pressure of the fixed impeller of calming the anger
Fore-and-aft direction of the diameter of gas active impeller along central rotating shaft successively decreases step by step.
Preferably, the turbine be connected including a front end with combustion chamber be integrated, rear end is with protecting outer barrel cover to dock
The turbine casing of one, several be placed in the motor activity rotated in turbine casing and under the drive of central rotating shaft
Impeller and several power being placed in turbine casing fix impeller, and the power fixes impeller and motor activity impeller edge
The fore-and-aft direction of central rotating shaft is distributed in interleaved, and the power fixes the diameter of impeller and the diameter of motor activity impeller
It is incremented by step by step along the fore-and-aft direction of central rotating shaft.
As a result of such scheme, the characteristics of utilizing pressure difference and the temperature difference of the invention, in the same of body discharge high-temp waste gas
When can complete the suction of cooling air, so as to not interfere with the exhaust efficiency (or operating efficiency) of body not only, and can reach
To the cooling effect of the part such as the second bearing of the exhaust end to body and support column, above-mentioned part can be effectively avoided to grow
Phase is in hot environment, improves body service life and the stability of work；Its is simple and compact for structure, operating efficiency not by
The cooling effect to end component can be ensured in the case of influence, there is very strong practical value and market popularization value.
Brief description of the drawings
Fig. 1 is the part section structural representation of the embodiment of the present invention；
Fig. 2 is the axial cross section structural representation of the cooling device of the embodiment of the present invention.
Embodiment
Embodiments of the invention are described in detail below in conjunction with accompanying drawing, but the present invention can be defined by the claims
Implement with the multitude of different ways of covering.
As depicted in figs. 1 and 2, a kind of gas turbine that the present embodiment provides, it includes sequentially being distributed and being connected being integrated
Compressor a, combustion chamber b, turbine c and cooling device d and through compressor a, combustion chamber b and turbine c distribution
Central rotating shaft e；Wherein, central rotating shaft e front end is assemblied in compressor a air intake, rear end then by by clutch shaft bearing f
Two bearing g are assemblied in turbine c exhaust end；Cooling device d docks what is be integrated including one with turbine c exhaust end port
The outer barrel cover 10 and one of protection is placed in the outer barrel cover 10 of protection and is in barrel cover 20 in the protection being coaxially distributed with protecting outer barrel cover 10,
In protecting outer barrel cover 10 and protecting between barrel cover 20 and along second bearing g radial direction ring it is all several be distributed with pass through
The air guide barrel cover 30 that space in protection between barrel cover 20 and second bearing g is connected with turbine c exhaust end port, every
One is provided with individual air guide barrel cover 30 to be used for second bearing g periphery wall with protecting the internal perisporium of outer barrel cover 10 to be connected as a single entity
Support column 40, meanwhile, on the perisporium for protecting outer barrel cover 10 and be located in the profile of each air guide barrel cover 30 and open up
There is at least one cold air main-inlet h, formed with protecting outer barrel cover 10 and protecting between adjacent two air guide barrel covers 30
Waste gas passing away k in area of space between barrel cover 20, and waste gas passing away k and turbine c exhaust end port phase
Connection.
Thus, after central rotating shaft e startups, compressor a is delivered to combustion after the air of engine body exterior being sucked and compressed
Burn in the b of room, then with the fuel mixed combustion in the b of combustion chamber, high-temperature fuel gas, which is flowed into turbine c, is promoting turbine c to carry out
Externally while acting, substantial amounts of high-temp waste gas will can be discharged from its exhaust port to engine body exterior；Now, due to cooling device
Setting, during high-temperature exhaust emission can turbine c exhaust port (i.e.：The rear end of turbine c impeller
In region) negative pressuren zone is formed, the engine body exterior cooling air relatively low compared to the temperature of high-temp waste gas can be via cooling main-inlet
Barrel cover 20 is sucked up in turbine c exhaust port h --- air guide barrel cover 30 --- in protection, so that with high-temp waste gas together
Discharged to outside body, and the heat that the part such as support column 40 and second bearing g in cooling air flow path is assembled
The air that can be cooled is brought to turbine c exhaust port, so as to realize to parts such as support column 40, second bearing g
Cooling effect.Based on this, the characteristics of using pressure difference and the temperature difference, cooling air can be completed while body discharges high-temp waste gas
Suction, so as to not interfere with the exhaust efficiency (or operating efficiency) of body not only, and the exhaust end group to body can be reached
It into the effect of part cooling, can effectively avoid above-mentioned part from being chronically in hot environment, improve body service life and work
The stability of work.
To optimize the structure of whole body to greatest extent, while ensure to greatest extent to portions such as second bearing g
The cooling effect of part, the outer barrel cover 10 of protection of the present embodiment include the periphery that a front port butts up against turbine c exhaust port
The outer barrel cover 11 and one of outer layer on side is placed in the outer barrel cover 11 of outer layer and protection between barrel cover 20 and front port butts up against turbine c
Exhaust port inner circumferential side on the outer barrel cover 12 of internal layer, between barrel cover 11 and be located at cold air outside internal layer inner cylinder cover 12 and outer layer
Main-inlet h rear end side is arranged at formed with several and the one-to-one additional-air inlet chamber m of air guide barrel cover 30, air guide barrel cover 30
Between barrel cover 20 and by additional-air inlet chamber m and protection between barrel cover 20 and second bearing g in barrel cover 12 and protection in internal layer
Space is connected, and the periphery wall of the internal perisporium of barrel cover outside outer layer 11 and second bearing g is connected as a single entity by support column 40；Outside outer layer
It is further opened with least one with additional-air inlet chamber m being connected on the perisporium of barrel cover 11 and positioned at each cold air main-inlet h rear end side
The auxiliary entrance n of logical cold air.Thus, when high-temp waste gas discharges via waste gas passing away k to outside body, cooling air have it is cold
While gas main-inlet h is entered in air guide barrel cover 30, also air guide barrel cover can be entered by cold air auxiliary entrance n and additional-air inlet chamber m
In 30, so as to effectively increase the air conditioning quantity entered in air guide barrel cover 30, ensured with this to support column 40 and second bearing g etc.
The cooling of part.
For avoid between the cooling air entered by the cold air main-inlet h cooling airs entered and by the auxiliary entrance n of cold air because
Occur interfering and influenceing the amount entered in air guide barrel cover 30, formed with a U-shaped ring on the periphery wall of outer layer outer barrel cover 11
Groove 13, cold air main-inlet h are located in U-shaped annular groove 13, meanwhile, the vertical range between cold air main-inlet h and central rotating shaft e is less than
Vertical range between cold air auxiliary entrance n and central rotating shaft e.Thus, can be anti-using the difference in height between two kinds of cold air inlets
The periphery of the outer barrel cover 11 of shield forms different inlet channels, to coordinate the change of pressure difference of the high-temp waste gas in discharge process, from
And ensureing cooling air can try one's best more enter in air guide barrel cover 30.
To extend the flow path of cooling air as far as possible, ensure to carry out the part near cooling air flow path
Cooling down, one is provided with along barrel cover outside outer layer on the internal perisporium of outer layer outer barrel cover 11 and positioned at the rear end side of U-shaped annular groove 13
11 axial directional distribution and the spoiler 14 in additional-air inlet chamber m.Thus, it can make what is entered via the auxiliary entrance n of cold air
Cooling air can be in that the axial direction for being similar to " S " type is sucked up in air guide barrel cover 30.
To disperse cooling air to greatest extent, enable equably to enter via the cooling air that the auxiliary entrance n of cold air enters
Enter in air guide barrel cover 30, so as to being cooled down from the surrounding of support column 40 to it, in additional-air inlet chamber m and be located at outer layer
Several axial direction distributions along barrel cover outside outer layer 11 are additionally provided between outer barrel cover 11 and spoiler 14 and each other along outside outer layer
The flow distribution plate 15 of the circumferential direction uniform intervals distribution of barrel cover 11.
To ensure that high-temp waste gas can discharge completely from waste gas passing away k to engine body exterior, high-temp waste gas is avoided to enter
Cooling after in space in protection between barrel cover 20 and second bearing g or central rotating shaft e to second bearing g causes unfavorable shadow
Ring, barrel cover 20 is back-end closure, the tubular structure body of front opening in the protection of the present embodiment.In this way, cooling air can be by preventing
The front port of barrel cover 20 enters in turbine c exhaust port in shield, and high-temp waste gas will not be then invaded in protection in barrel cover 20,
Now, cooling air can also be used certain effect that cools is played to turbine c impeller.
As a preferred scheme, to ensure the compression effectiveness to extraneous air, before the compressor a of the present embodiment includes one
End is integrated by clutch shaft bearing f with central rotating shaft e front end assembling, rear end is connected the compressor machine being integrated with combustion chamber b
Shell 50, several be placed in rotated in compressor casing 50 and under central rotating shaft e drive calm the anger active impeller 51 with
And several fixed impellers 52 of calming the anger for being placed in compressor casing 50, wherein, calm the anger fixed impeller 52 and active impeller of calming the anger
51 are distributed along central rotating shaft e fore-and-aft direction in interleaved, and the diameter for fixed impeller 52 of calming the anger and active impeller of calming the anger
Fore-and-aft direction of 51 diameter along central rotating shaft e successively decreases step by step.So as to using fixed impeller and active impeller in being spaced apart and
The effect that diameter successively decreases is realized and extraneous air is effectively compressed, and is mixed with being delivered in the b of combustion chamber with fuel.
As a preferred scheme, the turbine c of the present embodiment be connected including a front end with combustion chamber b be integrated, rear end
With protecting that outer barrel cover 11 docks the turbine casing 60 being integrated, that several are placed in turbine casing 60 is interior and in central rotating shaft e
Drive under the motor activity impeller 61 that is rotated and several power being placed in turbine casing 60 fix impellers 62,
Power is fixed impeller 62 and is distributed with fore-and-aft direction of the motor activity impeller 61 along central rotating shaft e in interleaved, and power is consolidated
Determine the diameter of impeller 62 with fore-and-aft direction of the diameter of motor activity impeller 61 along central rotating shaft e to be step by step incremented by.Thus, using solid
It is in be spaced apart and the effect of increasing diameter realizes release step by step to high-temperature fuel gas to determine impeller and active impeller, and then is realized pair
Outer acting and the discharge of waste gas.
The preferred embodiments of the present invention are the foregoing is only, are not intended to limit the scope of the invention, every utilization
The equivalent structure or equivalent flow conversion that description of the invention and accompanying drawing content are made, or directly or indirectly it is used in other correlations
Technical field, be included within the scope of the present invention.
Claims (8)
1. a kind of gas turbine, it includes order and is distributed and is connected the compressor being integrated, combustion chamber and turbine and runs through
In the central rotating shaft of compressor, combustion chamber and turbine distribution, the front end of the central rotating shaft is assemblied in pressure by clutch shaft bearing
The air intake of mechanism of qi, rear end are assemblied in the exhaust end of turbine by second bearing, it is characterised in that：It also includes a cooling and filled
Put；
The cooling device including one docked with the exhaust end port of turbine the outer barrel cover of the protection being integrated and one be placed in it is anti-
It is in barrel cover in the protection being coaxially distributed in the outer barrel cover of shield and with protecting outer barrel cover, barrel cover and in protecting between barrel cover outside the protection
And along second bearing radial direction ring it is all be distributed with several by the space in protection between barrel cover and second bearing with
The air guide barrel cover that the exhaust end port of turbine is connected, one is each provided with the air guide barrel cover and is used for second bearing
Periphery wall with protecting the support column that the internal perisporium of outer barrel cover is connected as a single entity, on the perisporium of the outer barrel cover of the protection and positioned at each
At least one cold air main-inlet is offered in the profile of air guide barrel cover, is formed between adjacent two air guide barrel covers
There is waste gas passing away, the waste gas passing away is connected with the exhaust end port of turbine.
A kind of 2. gas turbine as claimed in claim 1, it is characterised in that：The outer barrel cover of the protection is docked including a front port
Be placed in outside outer layer in barrel cover and protection between barrel cover in barrel cover outside the outer layer on the outer circumferential side of the exhaust port of turbine and one and
Front port butts up against the outer barrel cover of internal layer on the inner circumferential side of the exhaust port of turbine, barrel cover and the outer barrel cover of outer layer in the internal layer
Between and positioned at cold air main-inlet rear end side formed with several and the one-to-one additional-air inlet chamber of air guide barrel cover, it is described to lead
Inflator cover be arranged in internal layer in barrel cover and protection between barrel cover and by additional-air inlet chamber and barrel cover and second bearing in protection it
Between space be connected, the periphery wall of the internal perisporium of barrel cover outside outer layer and second bearing is connected as a single entity by the support column；It is described
On the perisporium of the outer barrel cover of outer layer and positioned at each cold air main-inlet rear end side be further opened with it is at least one with additional-air inlet chamber phase
The auxiliary entrance of cold air of connection.
A kind of 3. gas turbine as claimed in claim 2, it is characterised in that：On the periphery wall of the outer barrel cover of the outer layer formed with
One U-shaped annular groove, the cold air main-inlet are located in U-shaped annular groove, the vertical range between the cold air main-inlet and central rotating shaft
Less than the vertical range between the auxiliary entrance of cold air and central rotating shaft.
A kind of 4. gas turbine as claimed in claim 3, it is characterised in that：On the internal perisporium of the outer barrel cover of the outer layer and it is located at
The rear end side of U-shaped annular groove is provided with an axial directional distribution along barrel cover outside outer layer and the spoiler positioned at additional-air inlet intracavitary.
A kind of 5. gas turbine as claimed in claim 4, it is characterised in that：The additional-air inlet intracavitary and it is located at outer layer outer barrel
Several are additionally provided between cover and spoiler to be distributed and each other along the circumference of barrel cover outside outer layer along the axial of barrel cover outside outer layer
The flow distribution plate of direction uniform intervals distribution.
A kind of 6. gas turbine as any one of claim 1-5, it is characterised in that：Barrel cover is rear end in the protection
Closing, the tubular structure body of front opening.
A kind of 7. gas turbine as claimed in claim 6, it is characterised in that：The compressor passes through first axle including a front end
Hold with the front end of central rotating shaft assembling be integrated, rear end is connected the compressor casing being integrated with combustion chamber, several are placed in pressure
Rotated in mechanism of qi casing and under the drive of central rotating shaft calm the anger active impeller and several be placed in compressor casing
Interior fixed impeller of calming the anger, the fixed impeller of calming the anger are in interleaved with fore-and-aft direction of the active impeller along central rotating shaft of calming the anger
Distribution, and fore-and-aft direction of the diameter of the diameter of the fixed impeller of calming the anger and active impeller of calming the anger along central rotating shaft is passed step by step
Subtract.
A kind of 8. gas turbine as claimed in claim 6, it is characterised in that：The turbine includes a front end and held in the mouth with combustion chamber
It is connected in one, rear end docks the turbine casing being integrated with the outer barrel cover of protection, several are placed in turbine casing and in
The motor activity impeller rotated under the drive of heart rotating shaft and several power being placed in turbine casing fix impeller,
The power is fixed impeller and is distributed with fore-and-aft direction of the motor activity impeller along central rotating shaft in interleaved, and the power is consolidated
Determine the diameter of impeller with fore-and-aft direction of the diameter of motor activity impeller along central rotating shaft to be step by step incremented by.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710750436.6A CN107559091A (en) | 2017-08-28 | 2017-08-28 | A kind of gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710750436.6A CN107559091A (en) | 2017-08-28 | 2017-08-28 | A kind of gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107559091A true CN107559091A (en) | 2018-01-09 |
Family
ID=60976000
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710750436.6A Pending CN107559091A (en) | 2017-08-28 | 2017-08-28 | A kind of gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107559091A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111298929A (en) * | 2019-12-10 | 2020-06-19 | 广州达都动力科技有限公司 | Low-speed operable jet propulsion unit |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101743391A (en) * | 2008-01-10 | 2010-06-16 | 三菱重工业株式会社 | Exhaust section structure of gas turbine and gas turbine |
| CN101978138A (en) * | 2008-03-28 | 2011-02-16 | 三菱重工业株式会社 | Gas turbine |
| CN104066954A (en) * | 2012-02-23 | 2014-09-24 | 三菱日立电力***株式会社 | Gas turbine |
| CN104769225A (en) * | 2012-10-30 | 2015-07-08 | 西门子公司 | Temperature control within a cavity of a turbine engine |
| CN104919140A (en) * | 2013-01-22 | 2015-09-16 | 西门子能量股份有限公司 | Purge and cooling air for an exhaust section of a gas turbine assembly |
| CN204921169U (en) * | 2015-07-09 | 2015-12-30 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Gas turbine exhaust section structure |
| CN205036457U (en) * | 2015-08-27 | 2016-02-17 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Gas turbine exhaust casing cooling device |
| CN106321166A (en) * | 2015-06-17 | 2017-01-11 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Gas turbine supporting column cooling structure |
| US20170241295A1 (en) * | 2014-10-29 | 2017-08-24 | Mitsubishi Hitachi Power Systems, Ltd. | Exhaust system and gas turbine |
-
2017
- 2017-08-28 CN CN201710750436.6A patent/CN107559091A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101743391A (en) * | 2008-01-10 | 2010-06-16 | 三菱重工业株式会社 | Exhaust section structure of gas turbine and gas turbine |
| CN101978138A (en) * | 2008-03-28 | 2011-02-16 | 三菱重工业株式会社 | Gas turbine |
| CN104066954A (en) * | 2012-02-23 | 2014-09-24 | 三菱日立电力***株式会社 | Gas turbine |
| CN104769225A (en) * | 2012-10-30 | 2015-07-08 | 西门子公司 | Temperature control within a cavity of a turbine engine |
| CN104919140A (en) * | 2013-01-22 | 2015-09-16 | 西门子能量股份有限公司 | Purge and cooling air for an exhaust section of a gas turbine assembly |
| US20170241295A1 (en) * | 2014-10-29 | 2017-08-24 | Mitsubishi Hitachi Power Systems, Ltd. | Exhaust system and gas turbine |
| CN106321166A (en) * | 2015-06-17 | 2017-01-11 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Gas turbine supporting column cooling structure |
| CN204921169U (en) * | 2015-07-09 | 2015-12-30 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Gas turbine exhaust section structure |
| CN205036457U (en) * | 2015-08-27 | 2016-02-17 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Gas turbine exhaust casing cooling device |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111298929A (en) * | 2019-12-10 | 2020-06-19 | 广州达都动力科技有限公司 | Low-speed operable jet propulsion unit |
| CN111298929B (en) * | 2019-12-10 | 2020-10-09 | 东阳格盘机械科技有限公司 | Low-speed operable jet propulsion unit |
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Application publication date: 20180109 |
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| RJ01 | Rejection of invention patent application after publication |