CN101865034B - Air inlet bending head reinforced shock absorption structure of internal combustion turbine - Google Patents
Air inlet bending head reinforced shock absorption structure of internal combustion turbine Download PDFInfo
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- CN101865034B CN101865034B CN 201010201014 CN201010201014A CN101865034B CN 101865034 B CN101865034 B CN 101865034B CN 201010201014 CN201010201014 CN 201010201014 CN 201010201014 A CN201010201014 A CN 201010201014A CN 101865034 B CN101865034 B CN 101865034B
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Abstract
The invention relates to an air inlet bending head reinforced shock absorption structure of an internal combustion turbine, which comprises an internal combustion turbine air inlet system bending passage, an internal combustion turbine air inlet system bending head, a connecting plate and an internal combustion turbine air inlet system vertical section. The invention is characterized in that a reinforcing structure is arranged outside an internal combustion turbine air inlet system bending passage case, and a reinforced structure and a shock absorption structure are arranged outside the internal combustion turbine air inlet system bending head case. The invention realizes the integrated design of the air inlet bending reinforced shock absorption structure of the internal combustion turbine, adopts the combination forms of the reinforcing structures of I-shaped steel, H-shaped steel, channel steel and the like, and improves the damage-resistance intensity of the internal combustion turbine air inlet bending passage, and adopts the shock absorption structure for realizing the unloading of the bending part on the vibration effect. The structural design is novel and reasonable, and the invention has wide practical application value.
Description
Technical field
Patent of the present invention relates to a kind of reinforced shock absorption structure, especially a kind of reinforced shock absorption structure for the gas turbine inlet air system.
Background technique
Gas turbine power generation has efficiently, cleans, pollutes the advantages such as few, gas turbine unit can start, respond and load load fast under the state of emergency, be suitable as the power supply of peak load in emergency use and electrical network, can ensure preferably safety and the operation of electrical network.
The gas turbine inlet air system is the important auxiliary system of gas turbine, has bulky, baroque characteristics, and it is carried out structural analysis, takes the technical measures of reinforcement reduction structure quake relatively difficult.On the other hand, due to tradition research mainly for the relation that affects between gas turbine body, firing chamber, blade shape, unit operation mode and gas turbine proficiency.Therefore, many researchs all concentrate on gas turbine body aspect, and less to the research of the aspects such as gas turbine inlet air system bend characteristic, reinforced shock absorption.In fact, gas flow situation in the structural design of gas turbine inlet air system bend and bend also has very important impact to the performance of gas turbine, and the designing quality of gas turbine inlet air system bend directly affects usability and the life-span of gas turbine.
Summary of the invention
The present invention will provide a kind of air inlet bending head reinforced shock absorption structure of internal combustion turbine, this structure makes the inlet flow field distortion of gas handling system bend should reach minimum, the bend exit flow is even, the pressure loss is little, reduction due to the vibration of air-flow whirling motion and baffler to the vibration of gas turbine inlet air system bend housing, in order to avoid cause the effective output of gas turbine to reduce and the fuel consumption rate increase causes the Efficiency Decreasing of whole power plant; Gas turbine is operated in preferably in range of operating parameters.
For achieving the above object, technological scheme of the present invention is: a kind of air inlet bending head reinforced shock absorption structure of internal combustion turbine, comprise vertical section of gas turbine inlet air system bend, gas turbine inlet air system elbow, connecting plate, gas turbine inlet air system, be characterized in: gas turbine inlet air system bend housing is provided with the reinforcement structure outward, and gas turbine inlet air system elbow housing is provided with strengthening structure and shock-damping structure outward.
The outer reinforcement structure of gas turbine inlet air system bend housing is made of I-steel, H shaped steel and channel-section steel, the strengthening segment housing outer periphery of bend is reinforced with two circle I-steel, the bend housing outer periphery H section steel reinforcement of two circles between I-steel, bend housing rearward end housing outer periphery is with some circle H section steel reinforcements, and the I-shaped steel ring is parallel with connecting plate with the H steel rings, bend housing rear end bottom vertical is reinforced with channel-section steel on H shaped steel direction, and bend housing ear end face is reinforced with the reinforcement steel of some parallel bend housing bottoms with two side faces;
The strengthening structure of gas turbine inlet air elbow is all vertical uniform with the back at the horizontal segment of elbow, the stiffening plate I-steel end-to-end of the horizontal segment of elbow and back and bend housing rear surface, angle is 45 °, strengthen with I-steel is fixing in the elbow initial position, I-steel external application channel-section steel is reinforced;
Gas turbine inlet air bend shock-damping structure comprises two flat boards, spring, and parallelogram linkage wherein has uniform aperture on flat board, and the dull and stereotyped outside connects with gas turbine inlet air system bend housing on one side, and another side is connected with strengthening steel; Connect parallelogram linkage by spring between two flat boards.
The invention has the beneficial effects as follows: realized the comprehensive Design of air inlet bending head reinforced shock absorption structure of internal combustion turbine, adopted I-steel, H shaped steel and channel-section steel etc. are strengthened the combining form of structure, have improved the resistance of failure of gas turbine inlet air bend; Adopt shock-damping structure to realize the unloading of elbow part to jarring effect, structural design is new reasonable, has actual application value widely.
Description of drawings
Fig. 1 is gas turbine inlet air elbow structure stereogram of the present invention;
Fig. 2 is that the gas turbine inlet air bend is along the flow field direction planimetric map;
Fig. 3 is the left view of Fig. 2;
Fig. 4 is the right elevation of Fig. 2;
Fig. 5 is gas turbine inlet air bend shock-damping structure schematic diagram of mechanism.
Embodiment
The present invention is further illustrated below in conjunction with accompanying drawing and embodiment.
The gas turbine inlet air system is the important component part of gas turbine, mainly is comprised of equipment components such as filter, expansion joint, silencing apparatus, bend, changeover portion, extension, compressors.
The gas turbine inlet air system bend of indication of the present invention is made of air inlet volute and shrink nozzle filtering between noise reduction parts and gas compressor.Be used for making main air flow before entering gas compressor by the radial transition of unit to axial, therefore the gas turbine inlet air air flue has the nonaxisymmetric structure characteristics of radial air inlet, axial exhaust, air stream through the air inlet air flue except producing flow losses, also can be turned back to 90 ° that axially produce by radial transition because of air-flow, flow in the non-axisymmetric of air intake port (being compressor inlet) cross section generation, therefore, the structural strength of gas turbine inlet air system bend and aeroperformance have important impact to the service behaviour of gas turbine.
As shown in Figure 1, air inlet bending head reinforced shock absorption structure of internal combustion turbine of the present invention, mainly by gas turbine inlet air system bend 1, gas turbine inlet air system elbow 2, connecting plate 3, gas turbine inlet air system vertically section 4, strengthen steel 5 and damper mechanism 6 forms.Wherein be evenly arranged baffler in gas turbine inlet air system bend 1, wherein connecting plate 3 mainly is connected with the gas handling system filtering section, the flange Connecting format that adopt more, wherein strengthen steel 5 and comprise I-steel 51, H shaped steel 52 and channel-section steel 53, mainly being subjected to curved member as main in its web plane, so strengthening segment mainly adopts I-steel 51 due to this bend housing; In order further to strengthen the intensity of privileged sites, H shaped steel 52 and channel-section steel 53 have been adopted on these positions in addition.The strengthening structure of gas turbine inlet air elbow is mainly the form that adopts at housing connection reinforcement steel, and the layout size of strengthening steel is vertical uniform, uniform distance at horizontal segment and back and calculates.By the simulation analysis to the gas turbine inlet air system, the stress maximum value of can going off the curve is positioned at the elbow knuckle section, that the inhomogeneous of air-flow may produce vortex phenomenon because gas enters curved segment by silencing apparatus simultaneously, the place of the easy vibration-generating of air inlet bend also concentrates on here, so the design of the reinforced shock absorption structure of elbow part is the important content that improves gas handling system bend intensity and anti-seismic performance.
As shown in Figure 2, along the flow field direction planimetric map, can find out along flow field direction the reinforcement steel setting type of bend surface of shell for the gas turbine inlet air bend.
As shown in Figure 3, be gas turbine inlet air bend Way in planimetric map, at reinforcement structure employing I-steel 52 end-to-ends of elbow part, angle is the form of 45 °, also will adopt I-steel 52 to strengthen in the elbow initial position simultaneously.
As shown in Figure 4, for gas turbine inlet air bend back planimetric map, can find out the reinforcement steel setting type in bend housing rear surface.For the intensity that guarantees elbow part satisfies system requirements, this face adopts I-steel 52 end-to-ends too in the reinforcement structure of elbow part, angle is the form of 45 °, also to adopt I-steel 52 to strengthen in the bend initial position, simultaneously in place that elbow begins most on the basis that I-steel is strengthened, adopt channel-section steel 53, to avoid the direction variation on the impact of structure.
As shown in Figure 5, be gas turbine inlet air bend shock-damping structure schematic diagram of mechanism, mainly formed by flat board 61, screw 62, nut 63, packing ring 64, spring 65 and parallelogram linkage 66.Wherein have uniform aperture on dull and stereotyped 61, sketch is take two as the example explanation, and is actual in connecting the plane length decision.Dull and stereotyped 61 the outside connects with housing on one side, with strengthen steel be connected on one side.According to the collapsible principle of parallelogram, when bend partly has generation of vibration, will be passed to parallelogram linkage 66 by spring 65, thereby make parallelogram linkage 66 do flexible and opening and closing alternating motion, thereby reach the purpose of damping.
Claims (1)
1. air inlet bending head reinforced shock absorption structure of internal combustion turbine, comprise gas turbine inlet air system's bend (1), gas turbine inlet air system's elbow (2), described gas turbine inlet air system's bend (1) housing is provided with the reinforcement structure outward, and described gas turbine inlet air system's elbow (2) housing is provided with strengthening structure and shock-damping structure (6) outward, it is characterized in that: the reinforcement structure outside described gas turbine inlet air system's bend (1) housing is by I-steel (51), H shaped steel (52) and channel-section steel (53) consist of, strengthening segment housing outer periphery I-steel (51) reinforcing of gas turbine inlet air system bend (1), bend housing outer periphery H shaped steel (52) reinforcing between two circle I-steel (51), gas turbine inlet air system bend (1) housing rearward end housing outer periphery is reinforced with some circle H shaped steel (52), and I-steel (51) is parallel with connecting plate (3) with H shaped steel (52), gas turbine inlet air system bend (1) housing rear end bottom vertical is reinforced with channel-section steel (53) on H shaped steel (52) direction, gas turbine inlet air system bend (1) housing ear end face is reinforced with the reinforcement steel (5) of some parallel gas turbine inlet air system's bend (1) housing bottoms with two side faces, the strengthening structure of described gas turbine inlet air system's elbow (2) is all vertical uniform with the back at the horizontal segment of gas turbine inlet air system's elbow (2), the stiffening plate of the horizontal segment of gas turbine inlet air system elbow (2) and back and gas turbine inlet air system's bend (1) housing rear surface is with I-steel (51) end-to-end, angle is 45 °, strengthen with I-steel (51) is fixing in gas turbine inlet air system's elbow (2) initial position, I-steel (51) external application channel-section steel (53) is reinforced, the shock-damping structure (6) of described gas turbine inlet air system's elbow (2) comprises two flat boards (61), spring (65), parallelogram connection-rod (66) mechanism, wherein have uniform aperture on dull and stereotyped (61), the outside of dull and stereotyped (61) connects with gas turbine inlet air system's bend (1) housing on one side, and another side is connected with strengthening steel (5), connect parallelogram connection-rod (66) mechanism by spring (65) between two flat boards (61).
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| CN 201010201014 CN101865034B (en) | 2010-06-12 | 2010-06-12 | Air inlet bending head reinforced shock absorption structure of internal combustion turbine |
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| CN 201010201014 CN101865034B (en) | 2010-06-12 | 2010-06-12 | Air inlet bending head reinforced shock absorption structure of internal combustion turbine |
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| CN101865034A CN101865034A (en) | 2010-10-20 |
| CN101865034B true CN101865034B (en) | 2013-05-08 |
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| CN113898414B (en) * | 2021-12-09 | 2022-03-18 | 成都中科翼能科技有限公司 | Reinforcing structure for preventing thermal vibration deformation of high-pressure rotor of gas turbine |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN200978721Y (en) * | 2006-07-26 | 2007-11-21 | 沈阳黎明航空发动机(集团)有限责任公司 | R0110 heavy gas turbine five-stage gas-discharging system |
| CN201116500Y (en) * | 2007-11-19 | 2008-09-17 | 浙江吉利汽车有限公司 | Inlet manifold |
| CN201396393Y (en) * | 2009-03-19 | 2010-02-03 | 尹学军 | Spring damping vibration isolator |
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- 2010-06-12 CN CN 201010201014 patent/CN101865034B/en active Active - Reinstated
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN200978721Y (en) * | 2006-07-26 | 2007-11-21 | 沈阳黎明航空发动机(集团)有限责任公司 | R0110 heavy gas turbine five-stage gas-discharging system |
| CN201116500Y (en) * | 2007-11-19 | 2008-09-17 | 浙江吉利汽车有限公司 | Inlet manifold |
| CN201396393Y (en) * | 2009-03-19 | 2010-02-03 | 尹学军 | Spring damping vibration isolator |
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