CN104675447A - Turbine cooling gas circuit of gas turbine - Google Patents
Turbine cooling gas circuit of gas turbine Download PDFInfo
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- CN104675447A CN104675447A CN201510051649.0A CN201510051649A CN104675447A CN 104675447 A CN104675447 A CN 104675447A CN 201510051649 A CN201510051649 A CN 201510051649A CN 104675447 A CN104675447 A CN 104675447A
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- turbine
- rotary shaft
- intermediate rotary
- gas circuit
- cooling gas
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Abstract
The invention relates to the technical field of gas turbines and discloses a turbine cooling gas circuit of a gas turbine. The turbine cooling gas circuit comprises a middle rotary shaft, a combustion pressure cylinder and a turbine disc, wherein the gap between the middle rotary shaft and the combustion pressure cylinder forms a rotor-stator cavity, the turbine disc is fixedly connected with the rear end of the middle rotary shaft, a plurality of radial holes communicated with the rotor-stator cavity are formed in the peripheral direction of the middle rotary shaft, and the radial holes are communicated to turbine rotors. By the turbine cooling gas circuit, the air entering the middle rotary shaft can be purified, the turbine rotors can be prevented from being blocked, the air containing impurities is injected into a main turbine runner to act on the turbine, and power and efficiency loss is avoided.
Description
Technical field
The present invention relates to gas turbine technology field, particularly relate to a kind of Gas Turbine cooling gas circuit.
Background technique
The continuous innovation of modern gas turbines technology and development, for improving the overall thermal efficiency of combustion engine, turbine inlet temperature constantly raises.Turbine rotor blade works under high temperature environment as high-speed rotary part simultaneously, and only rely on the raising of materials'use temperature cannot meet actual user demand, turbine rotor blade 7 must take the cooling of certain forms.The cooling air of turbine rotor blade 7 is generally bled from gas compressor 1, and along with cooling requires more and more higher, rate of air sucked in required demand is also increasing, will cause the decline of thermal efficiency of gas turbine.Therefore a kind of ideal method is, from the air that gas compressor 1 is extracted out, through supercooler 3, the temperature that gas compressor 1 is bled is reduced further, to reduce the flow of bleeding, increases the efficiency of cycle of complete machine.
But adopt this scheme to cool, an inevitable problem is exactly, the air that gas compressor 1 is extracted out contains impurity, when supercooler 3, also inevitably mix impurity simultaneously, if by this air Injection rotor containing impurity, turbine rotor blade 7 is cooled, easily causes impurity to block the cooling vent of turbine rotor blade 7, cause the damage of turbine rotor blade 7.
Existing scheme mainly arranges an air filter 4 below at cooler 3, filters the air containing impurity, then by air entraining pipe 5, cooling-air is passed into a turn quiet dish chamber 6, but utilizes air filter 4 to there is following shortcoming:
(1) air filter 4 inevitably brings the pressure loss, brings impact to the cooling of turbine rotor blade 7 and unit efficiency;
(2) increase air filter 4, will workload and the maintenance cost of unit operation maintenance be increased, and also can bring the rising of cost of production;
(3) conventional air filter, need to consume Partial shrinkage air to take away impurity, this part pressurized air directly will enter exhaust section usually, causes the loss of the power of the assembling unit and efficiency.
Summary of the invention
(1) technical problem that will solve
The technical problem that the present invention mainly solves how to design a kind of cooling gas circuit newly, can purify the air entered in intermediate rotary shaft, avoids blocking turbine rotor blade; Simultaneously by impure air Injection turbine sprue, to turbine acting, power efficiency is avoided to lose.
(2) technological scheme
In order to solve the problems of the technologies described above, the invention provides a kind of Gas Turbine cooling gas circuit, it comprises intermediate rotary shaft, combustion cylinder pressure and the turbine disk, gap between described intermediate rotary shaft and combustion cylinder pressure is formed and turns quiet dish chamber, the described turbine disk is fixedly connected with the rear end of described intermediate rotary shaft, described intermediate rotary shaft be circumferentially with the radial hole that multiple and described turn of quiet dish chamber be connected, circulation chamber is provided with in described intermediate rotary shaft, the described turbine disk be circumferentially with the axial bore that multiple and described circulation chamber is connected, described axial bore leads to turbine rotor blade.
Wherein, the described turbine disk is also provided with the oblique through hole be connected with described circulation chamber, described oblique through hole is communicated to next stage turbine rotor blade.
Wherein, described turn of quiet dish chamber is communicated with turbine sprue.
Wherein, described radial hole is distributed in described intermediate rotary shaft.
Wherein, be provided with Sealing between described intermediate rotary shaft and combustion cylinder pressure, described combustion cylinder pressure, the space formed between intermediate rotary shaft and Sealing are described turn of quiet dish chamber.
(3) beneficial effect
Compared with prior art, the present invention has the following advantages:
A kind of Gas Turbine cooling gas circuit provided by the invention, adopt intermediate rotary shaft be circumferentially with multiple with turn the radial hole that is connected of quiet dish chamber, circulation chamber is provided with in described intermediate rotary shaft, the turbine disk be circumferentially with the axial bore that multiple and described circulation chamber is connected, described axial bore leads to turbine rotor blade, under the centrifugal action of intermediate rotary shaft, to be thrown out of the air plankton entered in described radial hole, thus the air of the chamber that circulates is cleaned air free from foreign meter, and then avoid blocking turbine rotor blade.
Accompanying drawing explanation
Fig. 1 is the structural representation that the Gas Turbine of prior art purifies air;
Fig. 2 is the overall structure schematic diagram of a kind of Gas Turbine cooling of the present invention gas circuit.
In figure: 1: gas compressor; 2: combustion cylinder pressure; 3: cooler; 4: air filter; 5: air entraining pipe; 6: turn quiet dish chamber; 7: turbine rotor blade; 8: intermediate rotary shaft; 9: circulation chamber; 10: circulation gas circuit; 10a: the first circulation branch road; 10b: the second circulation branch road; 10b1: one-level cooling branch road; 10b2: secondary cooling branch road; 11: radial hole; 12: axial bore; 13: the turbine disk.
Embodiment
Below in conjunction with drawings and Examples, the specific embodiment of the present invention is described in further detail.Following instance for illustration of the present invention, but is not used for limiting the scope of the invention.
In describing the invention, it should be noted that, term " " center ", " longitudinal direction ", " transverse direction ", " on ", D score, " front ", " afterwards ", " left side ", " right side ", " vertically ", " level ", " top ", " end " " interior ", orientation or the position relationship of the instruction such as " outward " are based on orientation shown in the drawings or position relationship, only the present invention for convenience of description and simplified characterization, instead of indicate or imply that the device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore limitation of the present invention can not be interpreted as.In addition, term " first ", " second ", " the 3rd " etc. only for describing object, and can not be interpreted as instruction or hint relative importance.
In describing the invention, it should be noted that, unless otherwise clearly defined and limited, term " installation ", " being connected ", " connection " should be interpreted broadly, and such as, can be fixedly connected with, also can be removably connect, or connect integratedly; Can be mechanical connection, also can be electrical connection; Can be directly be connected, also indirectly can be connected by intermediary, can be the connection of two element internals.For the ordinary skill in the art, concrete condition above-mentioned term concrete meaning in the present invention can be understood.
In addition, in describing the invention, except as otherwise noted, the implication of " multiple ", " many ", " many groups " is two or more.
As shown in Figure 2, for a kind of Gas Turbine cooling gas circuit provided by the invention, it comprises intermediate rotary shaft 8, combustion cylinder pressure 2 and the turbine disk 13, gap between described intermediate rotary shaft 8 and combustion cylinder pressure 2 is formed and turns quiet dish chamber 6, particularly, also Sealing is provided with between described intermediate rotary shaft 8 and combustion cylinder pressure 2, described combustion cylinder pressure 2, the space formed between intermediate rotary shaft 8 and Sealing are described turn of quiet dish chamber 6, described turn of quiet dish chamber 6 is the circulation gas circuit 10 of cooled gas, and a part of gas through described turn of quiet dish chamber 6 forms the first circulation branch road 10a and flows into turbine sprue.The described turbine disk 13 is fixedly connected with the rear end of described intermediate rotary shaft 8, described intermediate rotary shaft 8 be circumferentially with the radial hole 11 that multiple and described turn of quiet dish chamber 6 be connected, form the second circulation branch road 10b road, multiple described radial hole 11 is preferably distributed in described intermediate rotary shaft 8, circulation chamber 9 is provided with in described intermediate rotary shaft 8, the described turbine disk 13 be circumferentially with the axial bore 12 that multiple and described circulation chamber 9 is connected, form one-level cooling branch road 10b1; Described axial bore 12 leads to turbine rotor blade 7, so that cooling turbine movable vane 7 and the described turbine disk 13.Under the centrifugal action of intermediate rotary shaft 8, will be thrown out of the air plankton entered in described radial hole 11, thus the air of the chamber 9 that circulates is cleaned air free from foreign meter, and then avoids blocking turbine rotor blade 7.
In order to cool multistage turbine movable vane 7, the described turbine disk 13 is also provided with the oblique through hole be connected with described circulation chamber 9, form secondary cooling branch road 10b2, described oblique through hole is communicated to next stage turbine rotor blade 7, for cooling next stage turbine rotor blade 7.
Wherein, described turn of quiet dish chamber 6 is communicated with turbine sprue, by impure air Injection turbine sprue, to turbine acting, avoids power efficiency to lose.
As can be seen from the above embodiments, novel in structural design of the present invention, is divided into multichannel by cooling gas circuit, and gas free from foreign meter is passed into intermediate rotary shaft 8, for cooling turbine movable vane 7, the gas containing impurity is passed into turbine sprue, avoids power loss.
The foregoing is only preferred embodiment of the present invention, not in order to limit the present invention, within the spirit and principles in the present invention all, any amendment done, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (5)
1. a Gas Turbine cooling gas circuit, it comprises intermediate rotary shaft, combustion cylinder pressure and the turbine disk, gap between described intermediate rotary shaft and combustion cylinder pressure is formed and turns quiet dish chamber, the described turbine disk is fixedly connected with the rear end of described intermediate rotary shaft, it is characterized in that, described intermediate rotary shaft be circumferentially with the radial hole that multiple and described turn of quiet dish chamber be connected, circulation chamber is provided with in described intermediate rotary shaft, the described turbine disk be circumferentially with the axial bore that multiple and described circulation chamber is connected, described axial bore leads to turbine rotor blade.
2. Gas Turbine cooling gas circuit as claimed in claim 1, it is characterized in that, the described turbine disk is also provided with the oblique through hole be connected with described circulation chamber, described oblique through hole is communicated to next stage turbine rotor blade.
3. Gas Turbine cooling gas circuit as claimed in claim 1, it is characterized in that, described turn of quiet dish chamber is communicated with turbine sprue.
4. Gas Turbine cooling gas circuit as claimed in claim 1, it is characterized in that, described radial hole is distributed in described intermediate rotary shaft.
5. Gas Turbine cooling gas circuit as claimed in claim 1, it is characterized in that, be provided with Sealing between described intermediate rotary shaft and combustion cylinder pressure, described combustion cylinder pressure, the space formed between intermediate rotary shaft and Sealing are described turn of quiet dish chamber.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510051649.0A CN104675447A (en) | 2015-01-30 | 2015-01-30 | Turbine cooling gas circuit of gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510051649.0A CN104675447A (en) | 2015-01-30 | 2015-01-30 | Turbine cooling gas circuit of gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104675447A true CN104675447A (en) | 2015-06-03 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510051649.0A Pending CN104675447A (en) | 2015-01-30 | 2015-01-30 | Turbine cooling gas circuit of gas turbine |
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| CN (1) | CN104675447A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106014486A (en) * | 2016-08-09 | 2016-10-12 | 上海电气燃气轮机有限公司 | Gas turbine cooling gas path and gas turbine |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4991391A (en) * | 1989-01-27 | 1991-02-12 | Westinghouse Electric Corp. | System for cooling in a gas turbine |
| US20040046326A1 (en) * | 2002-09-11 | 2004-03-11 | Mitsubishi Heavy Industries Ltd. | Gas turbine |
| US20040219008A1 (en) * | 2003-02-06 | 2004-11-04 | Snecma Moteurs | Ventilation device for a high pressure turbine rotor of a turbomachine |
| EP1506474A2 (en) * | 2002-03-05 | 2005-02-16 | Siemens Aktiengesellschaft | Method for generating an automation program |
| US20050050901A1 (en) * | 2003-09-04 | 2005-03-10 | Siemens Westinghouse Power Corporation | Part load blade tip clearance control |
| EP1892378A1 (en) * | 2006-08-22 | 2008-02-27 | Siemens Aktiengesellschaft | Gas turbine |
| CN204591360U (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 cooling gas circuit |
-
2015
- 2015-01-30 CN CN201510051649.0A patent/CN104675447A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4991391A (en) * | 1989-01-27 | 1991-02-12 | Westinghouse Electric Corp. | System for cooling in a gas turbine |
| EP1506474A2 (en) * | 2002-03-05 | 2005-02-16 | Siemens Aktiengesellschaft | Method for generating an automation program |
| US20040046326A1 (en) * | 2002-09-11 | 2004-03-11 | Mitsubishi Heavy Industries Ltd. | Gas turbine |
| US20040219008A1 (en) * | 2003-02-06 | 2004-11-04 | Snecma Moteurs | Ventilation device for a high pressure turbine rotor of a turbomachine |
| US20050050901A1 (en) * | 2003-09-04 | 2005-03-10 | Siemens Westinghouse Power Corporation | Part load blade tip clearance control |
| EP1892378A1 (en) * | 2006-08-22 | 2008-02-27 | Siemens Aktiengesellschaft | Gas turbine |
| CN204591360U (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 cooling gas circuit |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106014486A (en) * | 2016-08-09 | 2016-10-12 | 上海电气燃气轮机有限公司 | Gas turbine cooling gas path and gas turbine |
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Application publication date: 20150603 |
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