CN203548348U - Low-pressure compressor structure for aircraft-derived gas turbine - Google Patents
Low-pressure compressor structure for aircraft-derived gas turbine Download PDFInfo
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- CN203548348U CN203548348U CN201320604287.XU CN201320604287U CN203548348U CN 203548348 U CN203548348 U CN 203548348U CN 201320604287 U CN201320604287 U CN 201320604287U CN 203548348 U CN203548348 U CN 203548348U
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Abstract
The utility model relates to a low-pressure compressor structure for an aircraft-derived gas turbine. The low-pressure compressor structure is composed of an inlet casing component, a low-pressure compressor casing component and a low-pressure rotor, wherein the inlet casing component is composed of an inlet casing and an inlet rectifying blade; the low-pressure compressor casing component is composed of a low-pressure compressor casing and a stator blade component; the low-pressure rotor is composed of all-level working blades and a low-pressure compressor disc; an annular clapboard is designed in segments; the annular clapboard in the inlet casing component is composed of a front part and a rear part; the inlet casing component is divided into inner and outer annular channels by a front clapboard of the inlet casing; the outer annular channel is blocked by the front clapboard of the inlet casing; and the inner annular channel is arranged as an inlet air channel of the gas turbine. The low-pressure compressor structure for the aircraft-derived gas turbine has the advantages that the manufacturing cost and production cycle of the aircraft-derived gas turbine are effectively reduced under the condition of ensuring that the performances of the gas turbine comply with the design requirements, so that the earnings of the aircraft-derived gas turbine can be quickly increased.
Description
Technical field
The utility model relates to mechanical structure field, particularly a kind of boat remodeling gas turbine low pressure compressor structure.
Background technique
Navigate in remodeling gas turbine low pressure compressor structural design in the past, for reducing former aeroengine intake air flow, in design, conventionally adopt low pressure compressor casing and stator blade are redesigned, reduce stator part runner radial dimension; Low pressure compressor working blade adopts to be cut top or redesigns blade, reduces working blade blade tip diameter.Due to corresponding the reducing of stator part runner radial dimension, working blade blade root place diameter does not become, corresponding the reducing of low pressure compressor runner circulation area, the needs of assurance boat remodeling gas turbine inlet air mass flow and high and low pressure rotor coupling.This technology has now obtained extensive employing the through engineering approaches application of domestic boat remodeling gas turbine research and development department.
But today being growing more intense in combustion machine market competition, boat remodeling gas turbine cost is high, serious restriction boat remodeling gas turbine commercialization process, if low pressure compressor newly designs, manufactures low pressure compressor casing and stator blade, the development cost of low pressure compressor will account for the 50%-60% of total development cost, and this makes the manufacture cost of boat remodeling gas turbine be difficult to decline space.In addition, because needs are manufactured low pressure compressor casing and stator blade again, greatly extended the lead time of low pressure compressor.
Model utility content
The purpose of this utility model is by a small amount of transformation of the way and new system structure, coordinate calculative determination low pressure compressor channel size, making can be for the boat remodeling gas turbine low pressure compressor on ground, reach and both meet design performance requirement, can effectively reduce again development cost, spy provides a kind of boat remodeling gas turbine low pressure compressor structure.
The utility model provides a kind of boat remodeling gas turbine low pressure compressor structure, it is characterized in that: described boat remodeling gas turbine low pressure compressor structure, is comprised of inlet casing assembly 1, low pressure compressor casing assembly 2, low pressure rotor 3; Wherein inlet casing assembly 1 is comprised of inlet casing 101 and import straightener(stator) blade 102; Low pressure compressor casing assembly 2 is comprised of low pressure compressor casing, stator vane assembly; Low pressure compressor rotor is comprised of working blades at different levels and low pressure compressor dish 305;
On the basis of aeroengine compressor structure, increase toroidal membrane, corresponding low pressure compressor working blade utilizes the former aeroengine compressor working blade transformation of the way, reduces greatest diametrical dimension and changes blade tip angle; The internal diameter size of boat remodeling gas turbine low pressure compressor toroidal membrane and turn, stator radial clearance determined by low pressure compressor Pneumatic Calculation result;
Toroidal membrane aluminium material, takes segment design, and the toroidal membrane in inlet casing assembly 1 is specially dividing plate 103 and inlet casing rear bulkhead 104 before inlet casing by forward and backward two-part and forms; Before inlet casing, dividing plate 103 is divided into inside and outside two annular passs by inlet casing assembly 1, outer ring passage blocks by dividing plate before inlet casing 103, air can not be flowed in outer ring passage by 1 import of inlet casing assembly, interior annular pass is gas turbine inlet air passageways, when gas turbine is worked, air flows in this passage; Before inlet casing, dividing plate 103, along circumferentially cutting and the notch of import straightener(stator) blade 102 in this identical profile in position, passes import straightener(stator) blade 102 while being convenient to assemble; Inlet casing rear bulkhead 104 is domain structure, and internal diameter size is consistent with inlet casing rear bulkhead 103, and there is annular boss at forward and backward two ends, and front end inserts in the annular groove on the front dividing plate 103 of inlet casing; The import straightener(stator) blade radial dimension corresponding with inlet casing rear bulkhead 104 reduces;
The corresponding toroidal membrane of boat remodeling gas turbine low pressure compressor working blade is whole loop configuration, and the corresponding dividing plate of stator blade is that in every grade of stator vane assembly under calculative determination boat remodeling gas turbine low pressure compressor radial flow path size, spacer blocks is installed at each blade circular gap place; By the spacer blocks on the corresponding toroidal membrane of working blade and stator blade, former aeroengine runner is divided into inside and outside passage, internal channel forms boat remodeling gas turbine low pressure compressor runner, and external chennel communicates with inlet casing assembly external chennel, and forms dead space;
First order working blade toroidal membrane 210 two ends are provided with annular groove, and one end is connected with inlet casing rear bulkhead 104 rear end annular boss, and one end is connected with the fan-shaped boss in first order stator blade spacer blocks 211; First order working blade toroidal membrane 210 is installed fixing with low pressure compressor first order casing 201; Working blade toroidal membrane 212 two ends, the second level are provided with annular groove, be connected with the fan-shaped boss in fan-shaped boss and second level stator blade spacer blocks 213 in first order stator blade spacer blocks 211 respectively, second level working blade toroidal membrane 212 is installed fixing with low pressure compressor second level casing 203; Subsequent stages by that analogy; Rear class stator blade and the adjacent formation assembly 209 of outlet straightener(stator) blade, inner annular dividing plate divides forward and backward two-part composition, and front portion is divided into and at stator blade circular gap place, adds spacer blocks 219, utilizes baffle plate 217 and screw 218 fixedly to prevent from coming off; Rear section outlet straightener(stator) blade dividing plate 220 is whole loop configuration, is circumferentially cut with and can comprises the notch of outlet straightener(stator) blade in this position profile, makes to export straightener(stator) blade through outlet straightener(stator) blade dividing plate 220 after assembling.
At the inner toroidal membrane that increases of former motor low pressure compressor runner, according to gas turbine Pneumatic Calculation result, determine toroidal membrane radial dimension, by toroidal membrane, make low pressure compressor runner be divided into inside and outside two annular passs.When gas turbine is worked, air can only flow into from interior annular pass, and outer ring passage separates by toroidal membrane and forms sealing dead space, and then reduces low pressure compressor intake air flow.Because low pressure compressor channel size reduces, corresponding the reducing of low pressure compressor working blade blade tip at different levels size, boat remodeling gas turbine low pressure compressor working blades at different levels can be changed a social system on original aeroengine compressor working blades at different levels basis.
Low pressure compressor afterbody stator blade is contiguous with outlet straightener(stator) blade, and internal partition mode is stator blade employing spacer blocks structure, and outlet straightener(stator) blade adopts the domain and circumferentially cuts the notch structure corresponding to outlet straightener(stator) blade profile of this position.
Advantage of the present utility model:
Boat remodeling gas turbine low pressure compressor structure described in the utility model, guaranteeing that gas turbine performance meets under the prerequisite of designing requirement, effectively reduce manufacture cost and the manufacture cycle of boat remodeling gas turbine, and then can improve fast the effect of boat remodeling gas turbine income.
Accompanying drawing explanation
Below in conjunction with drawings and the embodiments, the utility model is described in further detail:
Fig. 1 is former aeroengine compressor structural representation;
Fig. 2 is boat remodeling gas turbine low pressure compressor structural representation;
Fig. 3 is boat remodeling gas turbine first order low pressure compressor casing and stator vane assembly structural representation;
Fig. 4 is the rear class low pressure compressor casing of boat remodeling gas turbine and stator vane assembly structural representation;
Figure comprises: inlet casing assembly 1; Inlet casing 101; Import straightener(stator) blade 102; Dividing plate 103 before inlet casing; Inlet casing rear bulkhead 104; Low pressure compressor casing assembly 2; First order low pressure compressor casing 201; First order stator vane assembly 202; Second level low pressure compressor casing 203; Second level stator vane assembly 204; Third level low pressure compressor casing 205; Third level stator vane assembly 206; Fourth stage low pressure compressor casing forward part 207; Fourth stage low pressure compressor casing rear section 208; Fourth stage stator vane assembly and outlet straightener(stator) blade assembly 209; First order working blade dividing plate 210; First order stator blade spacer blocks 211; Second level working blade dividing plate 212; Second level stator blade spacer blocks 213; Third level working blade dividing plate 214; Third level stator blade spacer blocks 215; Fourth stage working blade dividing plate 216; Baffle plate 217; Screw 218; Fourth stage stator blade spacer blocks 219; Outlet straightener(stator) blade dividing plate 220; Screw 221; Locking plate 222; Round platform 223; Low pressure compressor rotor 3; First order working blade 301; Second level working blade 302; Third level working blade 303; Fourth stage working blade 304; Compressor disc 305; Intermediary's casing 4.
Embodiment
Embodiment 1
The present embodiment provides a kind of boat remodeling gas turbine low pressure compressor structure, it is characterized in that: described boat remodeling gas turbine low pressure compressor structure, is comprised of inlet casing assembly 1, low pressure compressor casing assembly 2, low pressure rotor 3; Wherein inlet casing assembly 1 is comprised of inlet casing 101 and import straightener(stator) blade 102; Low pressure compressor casing assembly 2 is comprised of low pressure compressor casing, stator vane assembly; Low pressure compressor rotor is comprised of working blades at different levels and low pressure compressor dish 305;
On the basis of aeroengine compressor structure, increase toroidal membrane, corresponding low pressure compressor working blade utilizes the former aeroengine compressor working blade transformation of the way, reduces greatest diametrical dimension and changes blade tip angle; The internal diameter size of boat remodeling gas turbine low pressure compressor toroidal membrane and turn, stator radial clearance determined by low pressure compressor Pneumatic Calculation result;
Toroidal membrane aluminium material, takes segment design, and the toroidal membrane in inlet casing assembly 1 is specially dividing plate 103 and inlet casing rear bulkhead 104 before inlet casing by forward and backward two-part and forms; Before inlet casing, dividing plate 103 is divided into inside and outside two annular passs by inlet casing assembly 1, outer ring passage blocks by dividing plate before inlet casing 103, air can not be flowed in outer ring passage by 1 import of inlet casing assembly, interior annular pass is gas turbine inlet air passageways, when gas turbine is worked, air flows in this passage; Before inlet casing, dividing plate 103, along circumferentially cutting and the notch of import straightener(stator) blade 102 in this identical profile in position, passes import straightener(stator) blade 102 while being convenient to assemble; Inlet casing rear bulkhead 104 is domain structure, and internal diameter size is consistent with inlet casing rear bulkhead 103, and there is annular boss at forward and backward two ends, and front end inserts in the annular groove on the front dividing plate 103 of inlet casing; The import straightener(stator) blade radial dimension corresponding with inlet casing rear bulkhead 104 reduces;
The corresponding toroidal membrane of boat remodeling gas turbine low pressure compressor working blade is whole loop configuration, and the corresponding dividing plate of stator blade is that in every grade of stator vane assembly under calculative determination boat remodeling gas turbine low pressure compressor radial flow path size, spacer blocks is installed at each blade circular gap place; By the spacer blocks on the corresponding toroidal membrane of working blade and stator blade, former aeroengine runner is divided into inside and outside passage, internal channel forms boat remodeling gas turbine low pressure compressor runner, and external chennel communicates with inlet casing assembly external chennel, and forms dead space;
First order working blade toroidal membrane 210 two ends are provided with annular groove, and one end is connected with inlet casing rear bulkhead 104 rear end annular boss, and one end is connected with the fan-shaped boss in first order stator blade spacer blocks 211; First order working blade toroidal membrane 210 is installed fixing with low pressure compressor first order casing 201; Working blade toroidal membrane 212 two ends, the second level are provided with annular groove, be connected with the fan-shaped boss in fan-shaped boss and second level stator blade spacer blocks 213 in first order stator blade spacer blocks 211 respectively, second level working blade toroidal membrane 212 is installed fixing with low pressure compressor second level casing 203; Subsequent stages by that analogy; Rear class stator blade and the adjacent formation assembly 209 of outlet straightener(stator) blade, inner annular dividing plate divides forward and backward two-part composition, and front portion is divided into and at stator blade circular gap place, adds spacer blocks 219, utilizes baffle plate 217 and screw 218 fixedly to prevent from coming off; Rear section outlet straightener(stator) blade dividing plate 220 is whole loop configuration, is circumferentially cut with and can comprises the notch of outlet straightener(stator) blade in this position profile, makes to export straightener(stator) blade through outlet straightener(stator) blade dividing plate 220 after assembling.
At the inner toroidal membrane that increases of former motor low pressure compressor runner, according to gas turbine Pneumatic Calculation result, determine toroidal membrane radial dimension, by toroidal membrane, make low pressure compressor runner be divided into inside and outside two annular passs.When gas turbine is worked, air can only flow into from interior annular pass, and outer ring passage separates by toroidal membrane and forms sealing dead space, and then reduces low pressure compressor intake air flow.Because low pressure compressor channel size reduces, corresponding the reducing of low pressure compressor working blade blade tip at different levels size, boat remodeling gas turbine low pressure compressor working blades at different levels can be changed a social system on original aeroengine compressor working blades at different levels basis.
Low pressure compressor afterbody stator blade is contiguous with outlet straightener(stator) blade, and internal partition mode is stator blade employing spacer blocks structure, and outlet straightener(stator) blade adopts the domain and circumferentially cuts the notch structure corresponding to outlet straightener(stator) blade profile of this position.
Claims (2)
1. a boat remodeling gas turbine low pressure compressor structure, is characterized in that: described boat remodeling gas turbine low pressure compressor structure, is comprised of inlet casing assembly (1), low pressure compressor casing assembly (2) low pressure rotor (3); Wherein inlet casing assembly (1) is comprised of inlet casing (101) and import straightener(stator) blade (102); Low pressure compressor casing assembly (2) is comprised of low pressure compressor casing, stator vane assembly; Low pressure compressor rotor is comprised of working blades at different levels and low pressure compressor dish (305);
On the basis of aeroengine compressor structure, increase toroidal membrane, corresponding low pressure compressor working blade utilizes the former aeroengine compressor working blade transformation of the way, reduces greatest diametrical dimension and changes blade tip angle; The internal diameter size of boat remodeling gas turbine low pressure compressor toroidal membrane and turn, stator radial clearance determined by low pressure compressor Pneumatic Calculation result;
Toroidal membrane aluminium material, takes segment design, and the toroidal membrane in inlet casing assembly (1) is specially dividing plate (103) and inlet casing rear bulkhead (104) before inlet casing by forward and backward two-part and forms; Before inlet casing, dividing plate (103) is divided into inside and outside two annular passs by inlet casing assembly (1), outer ring passage blocks by dividing plate (103) before inlet casing, air can not be flowed in outer ring passage by inlet casing assembly (1) import, interior annular pass is gas turbine inlet air passageways, when gas turbine is worked, air flows in this passage; Before inlet casing, dividing plate (103), along circumferentially cutting and the notch of import straightener(stator) blade (102) in this identical profile in position, passes import straightener(stator) blade (102) while being convenient to assemble; Inlet casing rear bulkhead (104) is domain structure, and internal diameter size is consistent with inlet casing rear bulkhead (103), and there is annular boss at forward and backward two ends, and front end inserts in the annular groove on the front dividing plate (103) of inlet casing; The import straightener(stator) blade radial dimension corresponding with inlet casing rear bulkhead (104) reduces.
2. according to boat remodeling gas turbine low pressure compressor structure claimed in claim 1, it is characterized in that: the corresponding toroidal membrane of boat remodeling gas turbine low pressure compressor working blade is whole loop configuration, the corresponding dividing plate of stator blade is that in every grade of stator vane assembly under calculative determination boat remodeling gas turbine low pressure compressor radial flow path size, spacer blocks is installed at each blade circular gap place; By the spacer blocks on the corresponding toroidal membrane of working blade and stator blade, former aeroengine runner is divided into inside and outside passage, internal channel forms boat remodeling gas turbine low pressure compressor runner, and external chennel communicates with inlet casing assembly external chennel, and forms dead space;
First order working blade toroidal membrane (210) two ends are provided with annular groove, and one end is connected with inlet casing rear bulkhead (104) rear end annular boss, and one end is connected with the fan-shaped boss in first order stator blade spacer blocks (211); First order working blade toroidal membrane (210) is installed fixing with low pressure compressor first order casing (201); Second level working blade toroidal membrane (212) two ends are provided with annular groove, be connected with the fan-shaped boss in fan-shaped boss and second level stator blade spacer blocks (213) in first order stator blade spacer blocks (211) respectively, second level working blade toroidal membrane (212) is installed fixing with low pressure compressor second level casing (203); Subsequent stages by that analogy; Rear class stator blade and the outlet adjacent formation assembly of straightener(stator) blade (209), inner annular dividing plate divides forward and backward two-part composition, front portion is divided at stator blade circular gap place and adds spacer blocks (219), utilizes baffle plate (217) and screw (218) fixedly to prevent from coming off; Rear section outlet straightener(stator) blade dividing plate (220) is whole loop configuration, is circumferentially cut with and can comprises the notch of outlet straightener(stator) blade in this position profile, makes to export straightener(stator) blade through outlet straightener(stator) blade dividing plate (220) after assembling.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201320604287.XU CN203548348U (en) | 2013-09-27 | 2013-09-27 | Low-pressure compressor structure for aircraft-derived gas turbine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201320604287.XU CN203548348U (en) | 2013-09-27 | 2013-09-27 | Low-pressure compressor structure for aircraft-derived gas turbine |
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| CN203548348U true CN203548348U (en) | 2014-04-16 |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105484871A (en) * | 2015-11-23 | 2016-04-13 | 沈阳黎明航空发动机(集团)有限责任公司 | Vehicle-mounted gas turbine transformed from obsolete fanjet |
| CN105840551A (en) * | 2016-04-15 | 2016-08-10 | 上海交通大学 | Pneumatic implementation method for multi-operating-point high-load compressor blades |
| CN107061314A (en) * | 2017-03-28 | 2017-08-18 | 沈阳冠能燃气轮机科技有限公司 | The low-pressure compressor changed a social system using retired engine |
| CN108223429A (en) * | 2017-09-30 | 2018-06-29 | 中国航发沈阳发动机研究所 | The fancase of the domain not fault wall |
| CN109505773A (en) * | 2018-12-28 | 2019-03-22 | 中国船舶重工集团公司第七0三研究所 | A kind of helium low-pressure compressor integral seal structure |
| CN110552913A (en) * | 2018-05-31 | 2019-12-10 | 中国人民解放军陆军军事交通学院 | Electrically driven multistage centrifugal compressor device with cooling circulation function |
| CN111312058A (en) * | 2019-11-29 | 2020-06-19 | 中国科学院工程热物理研究所 | Test piece structure of gas compressor |
| CN113217418A (en) * | 2021-06-29 | 2021-08-06 | 中国科学院工程热物理研究所 | Pneumatic appearance structure of multistage axial compressor |
| CN113898472A (en) * | 2021-11-17 | 2022-01-07 | 上海电气燃气轮机有限公司 | Compressor modification method and compressor |
| CN113914999A (en) * | 2021-12-14 | 2022-01-11 | 成都中科翼能科技有限公司 | Gas turbine compressor assembling method |
| CN114922858A (en) * | 2022-07-21 | 2022-08-19 | 成都中科翼能科技有限公司 | Stator structure of low-pressure compressor of gas turbine and assembling method thereof |
| CN114320615B (en) * | 2021-12-13 | 2024-05-17 | 中国船舶重工集团公司第七0三研究所 | Rotatable guide vane rotating mechanism of gas turbine compressor |
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2013
- 2013-09-27 CN CN201320604287.XU patent/CN203548348U/en not_active Expired - Fee Related
Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105484871B (en) * | 2015-11-23 | 2017-05-24 | 沈阳黎明航空发动机(集团)有限责任公司 | Vehicle-mounted gas turbine transformed from obsolete fanjet |
| CN105484871A (en) * | 2015-11-23 | 2016-04-13 | 沈阳黎明航空发动机(集团)有限责任公司 | Vehicle-mounted gas turbine transformed from obsolete fanjet |
| CN105840551A (en) * | 2016-04-15 | 2016-08-10 | 上海交通大学 | Pneumatic implementation method for multi-operating-point high-load compressor blades |
| CN105840551B (en) * | 2016-04-15 | 2018-06-12 | 上海交通大学 | The pneumatic implementation method of multi-state point high load capacity compressor blade |
| CN107061314A (en) * | 2017-03-28 | 2017-08-18 | 沈阳冠能燃气轮机科技有限公司 | The low-pressure compressor changed a social system using retired engine |
| CN108223429A (en) * | 2017-09-30 | 2018-06-29 | 中国航发沈阳发动机研究所 | The fancase of the domain not fault wall |
| CN110552913A (en) * | 2018-05-31 | 2019-12-10 | 中国人民解放军陆军军事交通学院 | Electrically driven multistage centrifugal compressor device with cooling circulation function |
| CN109505773B (en) * | 2018-12-28 | 2023-09-08 | 中国船舶重工集团公司第七0三研究所 | Helium low-pressure compressor integral sealing structure |
| CN109505773A (en) * | 2018-12-28 | 2019-03-22 | 中国船舶重工集团公司第七0三研究所 | A kind of helium low-pressure compressor integral seal structure |
| CN111312058A (en) * | 2019-11-29 | 2020-06-19 | 中国科学院工程热物理研究所 | Test piece structure of gas compressor |
| CN111312058B (en) * | 2019-11-29 | 2022-02-25 | 中国科学院工程热物理研究所 | Test piece structure of gas compressor |
| CN113217418A (en) * | 2021-06-29 | 2021-08-06 | 中国科学院工程热物理研究所 | Pneumatic appearance structure of multistage axial compressor |
| CN113898472A (en) * | 2021-11-17 | 2022-01-07 | 上海电气燃气轮机有限公司 | Compressor modification method and compressor |
| CN114320615B (en) * | 2021-12-13 | 2024-05-17 | 中国船舶重工集团公司第七0三研究所 | Rotatable guide vane rotating mechanism of gas turbine compressor |
| CN113914999A (en) * | 2021-12-14 | 2022-01-11 | 成都中科翼能科技有限公司 | Gas turbine compressor assembling method |
| CN114922858A (en) * | 2022-07-21 | 2022-08-19 | 成都中科翼能科技有限公司 | Stator structure of low-pressure compressor of gas turbine and assembling method thereof |
| CN114922858B (en) * | 2022-07-21 | 2022-09-30 | 成都中科翼能科技有限公司 | Stator structure of low-pressure compressor of gas turbine and assembling method thereof |
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Address after: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Patentee after: AECC SHENYANG LIMING AERO-ENGINE Co.,Ltd. Address before: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Patentee before: Aecc Shenyang Liming Aero Engine Co., Ltd. |
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| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140416 |