CN1514110A - High efficiency compressor for gas turbine - Google Patents
High efficiency compressor for gas turbine Download PDFInfo
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- CN1514110A CN1514110A CNA031337406A CN03133740A CN1514110A CN 1514110 A CN1514110 A CN 1514110A CN A031337406 A CNA031337406 A CN A031337406A CN 03133740 A CN03133740 A CN 03133740A CN 1514110 A CN1514110 A CN 1514110A
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Abstract
A high efficient compressor comprises casing, boss rod, working impeller and static blade. The rotary guide vane is set at inlet of the compressor and air blead valve is set after stage of 5, 10 and 15; two continuous stages on heavy gas turbine are processing casing, as 1-3 stage of compressor wheel disc and blade is set with cantilever support; rotor length is shortened about one meter, 1-4 stage disc of compressor rotor and drum are connected by bolt, 5-10, 10-17 stage disc and drum are connected by electronic beam welding, 4 and 5 stage disc as well as 10 and 11 stage disc are connected by pins; the radiant induced air tube and decked sleeve are set between the compressor and turbine as they are fixed on internal hole of compressor disc by ring like pieces.
Description
Technical field
The present invention relates to the gas compressor that uses in a kind of gas turbine, especially suck working medium about gas turbine and send into the firing chamber after by the gas compressor compression and spray into the acting of in turbine, expanding after the fuel combustion, export to the gas compressor that generator for electricity generation or other machine tool are done function by transmission shaft.
Background technique
Gas compressor is one of critical piece in the gas turbine, and what directly reflect gas compressor performance index parameter is overall compression ratio, adiabatic compression efficient and stable operation nargin.
For realizing above-mentioned performance index, the present basic practice is on gas compressor arbor and compressor casing, alternately set up working blade and stator blade continuously successively separately, and constitute gas flow by a plurality of grades of series connection, its overall compression ratio, adiabatic compression efficient and stable operation nargin are the important indicators of gas compressor, and the level pressure ratio of existing most gas turbine blowers is about about 1.16.
Summary of the invention
Present situation at existing gas turbine blower level pressure ratio, the invention provides the efficient gas compressor of a kind of gas turbine, this gas compressor is a single shaft, 15 grades of axial-flow compressors, its total pressure ratio is 14.7, the average level pressure ratio is 1.196, compressor adiabatic compression efficient is 0.84, the stable operation nargin of gas compressor is greater than 12%, and for realizing above index, concrete technological scheme of the present invention is:
1, compressor inlet is provided with rotatable guide vane.After the 5th, 10,15 grade, be provided for the different operating state and coordinate the air bleed valve of venting, air velocity distribution, the postponement stall of two-stage employing to improve first, second level work blade tip of rotor continuously makes the processor box technology of single rotor declared working condition stable operation nargin greater than 12% level on the combustion machine.
2, compressor rotor 1-3 level compressor disk and blade adopt the overhanging structure of cantilever, shorten about 1 meter than conventional design rotor length.For improving balance quality, internal stress when reducing working rotor, all dishes of compressor rotor and drum have three kinds of different connection form, 1-4 level dish is that bolt connects, 5-10 level dish, 11～17 grades of electron beam weldings, 4 grades of dishes adopt radially with 5 grades of dish joints and 10 grades of dishes and 11 grades of dish joints, and the pin mode is connected.
3, for the cooling air of different pressures and temperature is provided to turbine dish and working blade, in this machine, be provided with a kind of rotor internal cavity cold air transmitting set of forming by radial air entraining pipe and layering sleeve pipe, cooling air is introduced rotor internal cavity from the drum barrel perforate of required level of drawing, the air of introducing is collected by the some radiating type pipes that distribute along garden week, send into the turbine rotor inner chamber along the inner layer sleeve stream, elder generation's cooling turbine wheel disc, be introduced into working blade again and remove the turbine blade of cooling down high-temperature, in rotor, layering sleeve pipe and radial air entraining pipe are fixed on the endoporus of compressor disc with ring part, and rotate with rotor.
The good effect of scheme of the present invention is to reach higher total pressure ratio with less progression, rotor journal shortens, quality descends, cost is low, operate steadily, stable operation nargin significantly improves, and guides the cooling air interference-free of different pressures, different temperatures into separately destination, has strengthened the particularly cooling effect of turbine later stages.The effect of radiating type gas collecting tube is to reduce the temperature rising that produces in the rotation effect of coiling chamber internal cause wheel disc because of air-flow, the layering sleeve pipe also plays heat screen except that steering flow effect reduces the temperature rising of cooling air in transmission course, adopts this scheme to increase substantially the cooling effect of turbine dish and blade.
Description of drawings:
Fig. 1: be structural principle sectional view of the present invention;
Fig. 2: be the vertical junction plane schematic representation of stator casing rear housing among Fig. 1;
Fig. 3: be stator casing front housing horizontal integration face schematic representation among Fig. 1.
Among the figure: 1, gas compressor, 2, adjustable guide vane, 3, gas compressor stator casing, 4, processor box, 5 gas compressor straightener(stator) blades, 6,1～15 grades of compressor blades, 7, rotor, 8,1～15 grade of wheel disc, 9, air vent, 10, radial air entraining pipe, 11, layering sleeve pipe, 12, back drum barrel load dish, 13,1～3 grades of dishes, 14, preceding axle journal, 15,5～10 grades of dishes, 16, the drum barrel tapping, 17,11～15 grades of dishes, 18, front housing, 19, rear housing.
Embodiment
A kind of heavy duty gas turbine is made up of gas compressor stator (3) and rotor (7) with gas compressor (1).Import adjustable guide vane (2) is installed, gas compressor straightener(stator) blade (5) etc. on the stator.1～15 grade of wheel disc (8) is installed on the rotor, 1～15 grade of compressor blade (6), drum barrel load dish (12) after preceding axle journal (14) and the two-stage, its rotor rear end and turbine rotor front end are connected to form integral rotor with bolt.
The flow channel shape of gas compressor adopts advanced Pneumatic design method to determine.The blade profile of working blade and straightener(stator) blade all adopts the blade profile of the low loss of high efficiency.It is 14.7 that the optimum organization of this gas compressor pneumatic design and blade type selecting makes it reach pressure ratio on 15 stage compressor structures, and operation point efficient 0.84, stable operation nargin are 12%, and the average level pressure ratio reaches 1.196 level.
Gas compressor has fully utilized the way of stable operation nargin under the various raising off working states.At compressor inlet adjustable inlet guide vane (2) is housed, on first and second grade casing inwall, is provided with processor casing structure (4), on wall, have several tilting sulculuses.It can improve the flow field of first and second level work blade tip air-flow of gas compressor, thereby postpones air-flow stall, enlarges stable operation nargin.In the 5th, 10 and 15 grades of outlet designs of gas compressor air vent (9) is arranged, adjust the stable operation nargin that discharge quantity can enlarge the gas compressor off rating.
The stator casing (3) of gas compressor is divided into two sections of front and back.Front housing (18) has the level boundary that the limit is installed, and rear housing (19) has vertical boundary that the limit is installed, and this design feature can guarantee the rigidity basically identical of casing combination back level and Vertical direction, strengthens the complete machine rigidity.
1～3 grade of dish of compressor rotor (13) is designed to the cantilever type of protracting, 4 grades of dishes and preceding axle journal (14) electron beam formation overall structure welded together, and 5～10 grades of dishes (15) and 11～15 grades of dishes (17) and two drum barrel stopping-off pieces are the cell cube that electron beam welding is welded into.1～4 grade of dish of rotor links to each other with bolt, adopts one group of radially pin linkage structure form between 4 grades of dishes, 5～10 grades of dishes and 11～15 grades of dish cell cubes.1～15 grade blade (6) is housed on 1～15 grade of dish.Is big characteristics of this gas compressor as the length and the present heavy single-rotor gas turbine that have shortened rotor in 1～3 grade of dish of figure rotor journal retraction greatly than it.The compressor rotor dish connect to adopt bolt, welding and the form of pin combination radially.Made things convenient for the enforcement of the substep balance scheme of rotor, improved balance quality of rotor, the internal stress when reducing working rotor also is one of this gas compressor characteristics.
Be to carry cooling air to the wheel disc and the blade of turbine, this programme adopts the turbine different fractions not carry the scheme of cooling air of different pressures, temperature to improve the cooling effect of every grade of turbine wheel disc and blade.Specific implementation method is the rotor internal cavity cooling air transmitting set that adopts radial air entraining pipe (10) and layering sleeve pipe (11) to form.Cooling air is introduced from drum barrel tapping (16), is collected by the some radial radiation shape air entraining pipes that are uniformly distributed along the circumference, and the wheel disc and the blade that transfer to turbine along the layering sleeve pipe of inner chamber cool off them.This device rotates with compressor rotor with the inner radius that ring part is fixed on the compressor rotor wheel disc.The effect of radiation air entraining pipe is to reduce the cooling air that enters rotor internal cavity to heat up because of the wheel disc rotation effect, the cooling air that different pressures and temperature are isolated in the effect of layering sleeve pipe on the one hand forms passage, also play the radiative heat transfer of the effect minimizing of heat screen in addition to cooling air, the characteristics of this technological scheme are to overcome in the heavy machine the not good enough shortcoming of cooling effect in the scheme of the sub-thread cooling air order cooling turbine wheel discs at different levels that adopt usually and blade, adopt this device can increase substantially the particularly cooling effect of what wheel disc and blade behind the turbine of cooling effect.
Claims (3)
1, a kind of gas turbine gas compressor, it includes casing, running wheel and stator blade, be characterized in that compressor inlet is provided with rotatable guide vane, the 5th, 10, after 15 grades air bleed valve is set, first, be provided with processor casing structure on the secondary casing inwall, 1～3 grade of compressor disk and blade are provided with cantilever support, 1～4 grade of dish of compressor rotor is connected with the drum bolt, 5～10,11～17 dishes are connected with the drum electron beam welding, 4 with 5 grades the dish and 10 with 11 grades the dish pins be connected, be provided with radial air entraining pipe and layering sleeve pipe between gas compressor and the turbine, be fixed on the compressor disc endoporus with ring part.
2, gas turbine blower as claimed in claim 1 is characterized in that being provided with processor casing structure on described first and second grade casing inwall, is to have some tilting sulculuses on wall.
3, gas turbine blower as claimed in claim 1, it is characterized in that in described rotor, being provided with a kind of rotor internal cavity cold air transmitting set of forming by radial air entraining pipe and layering sleeve pipe, in rotor, layering sleeve pipe and radial air entraining pipe are fixed on the endoporus of compressor disc with ring part, and rotate with rotor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB031337406A CN1301364C (en) | 2003-07-16 | 2003-07-16 | High efficiency compressor for gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB031337406A CN1301364C (en) | 2003-07-16 | 2003-07-16 | High efficiency compressor for gas turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1514110A true CN1514110A (en) | 2004-07-21 |
| CN1301364C CN1301364C (en) | 2007-02-21 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB031337406A Expired - Fee Related CN1301364C (en) | 2003-07-16 | 2003-07-16 | High efficiency compressor for gas turbine |
Country Status (1)
| Country | Link |
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| CN (1) | CN1301364C (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101460707B (en) * | 2006-06-02 | 2011-10-19 | 西门子公司 | Annular flow duct for a turbomachine through which a main flow can flow in the axial direction |
| CN103925244A (en) * | 2014-04-02 | 2014-07-16 | 清华大学 | Large-flow high-load axial compressor for 300MW F-class heavy-duty gas turbine |
| CN104359448A (en) * | 2014-11-07 | 2015-02-18 | 沈阳黎明航空发动机(集团)有限责任公司 | Continuous angle measurement device of intermediate case air bleed valve |
| CN104454025A (en) * | 2014-11-12 | 2015-03-25 | 中国科学院工程热物理研究所 | Cooling structure for high-temperature rotating wheel disc |
| CN105156214A (en) * | 2015-07-09 | 2015-12-16 | 中国航空工业集团公司沈阳发动机设计研究所 | Disc cavity gas collecting device for heavy-duty gas turbine |
| CN108457749A (en) * | 2018-01-22 | 2018-08-28 | 哈尔滨工程大学 | A kind of device of gas turbine inlet air zone of control spraying humidification |
| CN108757509A (en) * | 2018-05-30 | 2018-11-06 | 中国航发动力股份有限公司 | A kind of gas turbine low-pressure compressor structure |
| CN110566515A (en) * | 2019-09-22 | 2019-12-13 | 中国航发沈阳发动机研究所 | gas-entraining structure on inner side of gas compressor |
| CN111550435A (en) * | 2020-05-25 | 2020-08-18 | 中国航发沈阳发动机研究所 | Multistage rotor disk connection structure |
| CN113977061A (en) * | 2021-12-03 | 2022-01-28 | 中国航发燃气轮机有限公司 | Method for guaranteeing electron beam welding coaxiality of large-diameter drum barrel of gas turbine |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2554355Y (en) * | 2002-07-31 | 2003-06-04 | 上海汽轮机有限公司 | Axit-flow compressor stator blade rotaaling ring transmission |
-
2003
- 2003-07-16 CN CNB031337406A patent/CN1301364C/en not_active Expired - Fee Related
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101460707B (en) * | 2006-06-02 | 2011-10-19 | 西门子公司 | Annular flow duct for a turbomachine through which a main flow can flow in the axial direction |
| CN103925244A (en) * | 2014-04-02 | 2014-07-16 | 清华大学 | Large-flow high-load axial compressor for 300MW F-class heavy-duty gas turbine |
| CN103925244B (en) * | 2014-04-02 | 2017-03-15 | 清华大学 | A kind of big flow high load axial compressor and fan for 300MW F level heavy duty gas turbines |
| CN104359448B (en) * | 2014-11-07 | 2016-10-05 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of Middle casing air bleed valve angle continuous measuring device |
| CN104359448A (en) * | 2014-11-07 | 2015-02-18 | 沈阳黎明航空发动机(集团)有限责任公司 | Continuous angle measurement device of intermediate case air bleed valve |
| CN104454025A (en) * | 2014-11-12 | 2015-03-25 | 中国科学院工程热物理研究所 | Cooling structure for high-temperature rotating wheel disc |
| CN104454025B (en) * | 2014-11-12 | 2015-11-18 | 中国科学院工程热物理研究所 | A kind of cooling structure for High Temperature Rotating wheel disc |
| CN105156214A (en) * | 2015-07-09 | 2015-12-16 | 中国航空工业集团公司沈阳发动机设计研究所 | Disc cavity gas collecting device for heavy-duty gas turbine |
| CN108457749A (en) * | 2018-01-22 | 2018-08-28 | 哈尔滨工程大学 | A kind of device of gas turbine inlet air zone of control spraying humidification |
| CN108757509A (en) * | 2018-05-30 | 2018-11-06 | 中国航发动力股份有限公司 | A kind of gas turbine low-pressure compressor structure |
| CN110566515A (en) * | 2019-09-22 | 2019-12-13 | 中国航发沈阳发动机研究所 | gas-entraining structure on inner side of gas compressor |
| CN110566515B (en) * | 2019-09-22 | 2020-12-18 | 中国航发沈阳发动机研究所 | Gas-entraining structure on inner side of gas compressor |
| CN111550435A (en) * | 2020-05-25 | 2020-08-18 | 中国航发沈阳发动机研究所 | Multistage rotor disk connection structure |
| CN113977061A (en) * | 2021-12-03 | 2022-01-28 | 中国航发燃气轮机有限公司 | Method for guaranteeing electron beam welding coaxiality of large-diameter drum barrel of gas turbine |
| CN113977061B (en) * | 2021-12-03 | 2023-01-31 | 中国航发燃气轮机有限公司 | Method for guaranteeing electron beam welding coaxiality of large-diameter drum barrel of gas turbine |
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|---|---|
| CN1301364C (en) | 2007-02-21 |
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Granted publication date: 20070221 Termination date: 20160716 |
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| CF01 | Termination of patent right due to non-payment of annual fee |