CN105569741A - Gas turbine structure increasing initial temperature of gas - Google Patents
Gas turbine structure increasing initial temperature of gas Download PDFInfo
- Publication number
- CN105569741A CN105569741A CN201610074664.1A CN201610074664A CN105569741A CN 105569741 A CN105569741 A CN 105569741A CN 201610074664 A CN201610074664 A CN 201610074664A CN 105569741 A CN105569741 A CN 105569741A
- Authority
- CN
- China
- Prior art keywords
- blade
- gas turbine
- platform
- initial temperature
- gas
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/185—Liquid cooling
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/284—Selection of ceramic materials
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/603—Composites; e.g. fibre-reinforced
- F05D2300/6033—Ceramic matrix composites [CMC]
Abstract
The invention discloses a gas turbine structure increasing the initial temperature of gas. The gas turbine structure comprises a movable blade structure of a gas turbine. The movable blade structure comprises a blade body, a platform, a blade stem, a turbine disc and a blade root. The blade body is welded to the upper end of the platform. The blade stem is welded to the lower end of the platform. A structure that a plurality of teeth are engaged is adopted between the turbine disc and the blade root. Each of the blade body, the platform and a stem body of the blade stem is provided with a cooling liquid closing channel. Holes for heat dissipation are formed in the position, close to the center axis, of the blade root. Preferably, the blade body, the platform, the blade stem, the turbine disc and the blade root are made of fiber-reinforced ceramic matrix composites. According to the gas turbine structure, the closed cooling liquid structure, the heat dissipation hole structure and the high temperature and impact resisting ceramic materials are adopted, the key structure, namely the movable blade structure of the gas turbine can bear high-temperature instant impacts, and therefore the initial temperature of the gas turbine is greatly increased.
Description
Technical field
The present invention relates to a kind of gas turbine structure, particularly relate to a kind of gas turbine structure that can improve combustion gas initial temperature.
Background technique
Gas turbine is a kind of thermal power machinery of high speed rotary, along with the continuous progress of technology, the turbine-inlet temperature (i.e. combustion gas initial temperature) of industrial gas turbine has brought up to 1100 DEG C to 1200 DEG C, it is evident that, combustion gas initial temperature is higher, the acting of gas turbine is also just corresponding larger, this is also that combustion gas initial temperature is also in the reason constantly raised, but we also should see simultaneously, due to the thermal shock that high temperature produces gas turbine, thermal stress and thermal expansion, make the structural design of gas turbine, particularly high temperature circulation, the design of high temperature resistant part is faced with a series of problem, mainly be summarized as: the cooling of high temperature component, the hot position of heat radiation and component and cold position.
Summary of the invention
The present invention is exactly according to the problems referred to above, and propose a kind of gas turbine structure that can improve combustion gas initial temperature, this structure can bear the impact of higher initial temperature, thus makes the initial temperature of gas turbine higher, does work larger.
For reaching above-mentioned technical purpose, present invention employs a kind of gas turbine structure improving combustion gas initial temperature, comprise the movable vane structure of gas turbine, described movable vane structure comprises blade, platform, petiole, wheel disc and blade root, described blade is welded in the upper end of platform, described petiole is welded in platform lower end, multiple tooth is adopted to intermesh structure between described wheel disc and blade root, the handle of described blade, platform and petiole is equipped with cooling liquid with it and closes, and described blade root is provided with the hole for dispelling the heat near position, medial axis.
Preferably, described blade, platform, petiole, wheel disc and blade root are made by FRCMC.
The present invention adopts closed cooling liquid structure, radiation hole structure and stupalith that is high temperature resistant, that impact, makes the key structure of gas turbine--and movable vane structure can bear the moment impact of higher temperature, thus substantially increases the initial temperature of gas turbine.
Accompanying drawing explanation
Shown in Fig. 1 is apparatus structure schematic diagram of the present invention;
Wherein, 1, blade; 2, platform; 3, petiole; 4, wheel disc; 5, blade root; 6, cooling liquid is closed; 7, hole.
Embodiment
Embodiment is described in more detail the present invention below.
As shown in Figure 1, a kind of gas turbine structure improving combustion gas initial temperature, comprise the movable vane structure of gas turbine, this movable vane structure comprises blade 1, platform 2, petiole 3, wheel disc 4 and blade root 5, blade 1 is welded in the upper end of platform 2, and petiole 3 is welded in the lower end of platform 2, and adopts multiple tooth to intermesh structure between wheel disc 4 and blade root 5, be equipped with cooling liquid with it at the handle of blade 1, platform 2 and petiole 3 and close 6, and to be provided with the hole 7 for dispelling the heat near position, medial axis blade root 5.
Arrange after cooling liquid closes 6 with it at the handle of blade 1, platform 2 and petiole 3, the heat that blade 1, platform and petiole 3 can be made to produce instantaneously when High Rotation Speed is closed 6 by the cooling liquid being provided with cooling liquid and is dissipated, and hole 7 also plays the effect of auxiliary heat dissipation.
In the present invention, blade 1, platform 2, petiole 3, wheel disc 4 and blade root 5 are made by FRCMC.FRCMC take pottery as a class composite material of matrix and various fiber composite.Ceramic matrix can be the high-temperature structural ceramics such as silicon nitride, silicon carbide.These advanced ceramics have the excellent properties such as high temperature resistant, high strength and rigidity, relative weight be lighter, anticorrosive, and its fatal weakness is enbrittled, and when being in stress phase, can crack, and even fracture causes material failure.And adopt high strength, elastomeric fiber and matrix compound, be then the effective method improving ceramics toughness and reliability.Fiber can stop the expansion of crackle, thus obtains the FRCMC of excellent in toughness.
Generally speaking, the present invention adopts closed cooling liquid structure, radiation hole structure and stupalith that is high temperature resistant, that impact, making the key structure of gas turbine--movable vane structure can bear the moment impact of higher temperature, thus substantially increases the initial temperature of gas turbine.
Claims (2)
1. one kind is improved the gas turbine structure of combustion gas initial temperature, comprise the movable vane structure of gas turbine, described movable vane structure comprises blade, platform, petiole, wheel disc and blade root, described blade is welded in the upper end of platform, described petiole is welded in platform lower end, adopts multiple tooth to intermesh structure, it is characterized in that between described wheel disc and blade root, the handle of described blade, platform and petiole is equipped with cooling liquid with it and closes, and described blade root is provided with the hole for dispelling the heat near position, medial axis.
2. a kind of gas turbine structure improving combustion gas initial temperature as claimed in claim 1, it is characterized in that, described blade, platform, petiole, wheel disc and blade root are made by FRCMC.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610074664.1A CN105569741A (en) | 2016-02-03 | 2016-02-03 | Gas turbine structure increasing initial temperature of gas |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610074664.1A CN105569741A (en) | 2016-02-03 | 2016-02-03 | Gas turbine structure increasing initial temperature of gas |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105569741A true CN105569741A (en) | 2016-05-11 |
Family
ID=55880293
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610074664.1A Pending CN105569741A (en) | 2016-02-03 | 2016-02-03 | Gas turbine structure increasing initial temperature of gas |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105569741A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2839268A (en) * | 1950-01-18 | 1958-06-17 | Allis Chalmers Mfg Co | Gas turbine |
| US4212587A (en) * | 1978-05-30 | 1980-07-15 | General Electric Company | Cooling system for a gas turbine using V-shaped notch weirs |
| US6565312B1 (en) * | 2001-12-19 | 2003-05-20 | The Boeing Company | Fluid-cooled turbine blades |
| CN102200031A (en) * | 2010-03-22 | 2011-09-28 | 通用电气公司 | Apparatus for cooling a bucket assembly |
-
2016
- 2016-02-03 CN CN201610074664.1A patent/CN105569741A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2839268A (en) * | 1950-01-18 | 1958-06-17 | Allis Chalmers Mfg Co | Gas turbine |
| US4212587A (en) * | 1978-05-30 | 1980-07-15 | General Electric Company | Cooling system for a gas turbine using V-shaped notch weirs |
| US6565312B1 (en) * | 2001-12-19 | 2003-05-20 | The Boeing Company | Fluid-cooled turbine blades |
| CN102200031A (en) * | 2010-03-22 | 2011-09-28 | 通用电气公司 | Apparatus for cooling a bucket assembly |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20160511 |
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| WD01 | Invention patent application deemed withdrawn after publication |