CN102678590B - Ultra-compact high pressure ratio oblique flow-centrifugal combined compressor structure - Google Patents
Ultra-compact high pressure ratio oblique flow-centrifugal combined compressor structure Download PDFInfo
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Abstract
The invention discloses a kind of ultra-compact high pressure ratio oblique flow-centrifugal combined compressor structure, relate to gas compressor technology, it has inclined flow air compressor and centrifugal compressor two-stage, the first order is inclined flow air compressor, the second level is centrifugal compressor, and key adopts one section of minor diameter " S " type elbow connecting structure between inclined flow air compressor and centrifugal compressor.Structure of the present invention can be directly used in aero gas turbine engine, have that structure is simple, component are few, compact structure, reliability are high and processing maintenance cost is low etc. combines many advantages, the problem that the radial dimension that single-stage pressure ratio is low, progression is many, weight is large, manufacture cost is high and two stage centrifugal gas compressor exists that domestic existing middle-size and small-size aero gas turbine engine adopts multi stage axial flow compressor, axial-flow-centrifugal combined compressor to exist is large can be solved.
Description
Technical field
The present invention relates to gas compressor technical field, be a kind of ultra-compact high pressure ratio oblique flow-centrifugal combined compressor structure, it is specially adapted to high performance turbine gas turbine engine.
Background technique
In all kinds, low thrust aero gas turbine engine maximum difference is presented as compressor part type difference, all adopt the multi stage axial flow compressor structural type of large discharge, high pressure ratio different from high thrust aeroengine, middle low thrust aeroengine compression system all adopts combined compressor.But also have and to adopt holoaxial stream, as WS500, its high-pressure compressor have employed 5 grades of axial flow compressors, and the advantage of multiatage axial flow compressor is that runner is level and smooth, efficiency is high, but shortcoming is also obvious: 1. multi stage axial flow compressor amount of parts is many, cost is high; 2. low, the anti-foreign material deterioration characteristic of distortion tolerance is poor; 3. along with the raising of pressure ratio, the channel height of later stages is more and more less, and blade is short and thin, and when whole gas compressor all adopts axial flow level, the efficiency of later stages will be very low, add blade processing difficulty simultaneously; 4. axial flow compressor single-stage pressure ratio is low, for the motor needing high supercharging pressure level, as adopted multi stage axial flow compressor, will occur rotor dynamics problems because rotor span is long; 5. due to compact multi-level axial flow compressor inter-stage coupling difficulty, under middle and slow speed of revolution, the stability margin of gas compressor is less, in order to expand stable operation range, before usually adopting, what stator blade is adjustable or install air-release mechanism additional, complicated blade adjustments and the introducing of air-release mechanism and corresponding control system further increase structural complexity, make the raising of engine thrust-weight ratio encounter bottleneck.It is level and smooth that axial-flow-centrifugal/oblique flow combined compressor combines axial flow level runner, and efficiency is high and centrifugal level flow is little, and operating range is broad, and the feature that part is few and reliability is high, is widely used in the motor of medium-small flow.External several up-to-date model motor is as the T700 motor of GE company, and what the F107 motor of Williams & Associates and the TFE731 motor etc. of Honeywell Inc. all adopted is axial-flow-centrifugal combined compressor.But axial-flow-centrifugal combined compressor, due to the existence of axial flow level, is difficult to the above-mentioned drawback avoided existing for multi stage axial flow compressor equally; Two stage centrifugal gas compressor has that structure is simple, component are few, reliability is high and the advantage such as processing maintenance cost is low, but, two stage centrifugal gas compressor radial dimension is larger, increase wind-exposuring area and the weight of motor, and add the power acted on bearing, increase design bearing difficulty, reduce the life-span of bearing.Therefore, a kind of novel combined compressor topology layout of exploration is needed badly.
Summary of the invention
In order to overcome the problem existing for aeroengine multi stage axial flow compressor, axial-flow-centrifugal/oblique flow combined compressor and two stage centrifugal gas compressor, the object of the invention is to propose a kind of ultra-compact oblique flow-centrifugal combined compressor structure, it has, and structure is simple, component are few, compact structure, reliability are high and the processing many advantages such as maintenance cost is low.
In order to achieve the above object, technical solution of the present invention is:
A kind of ultra-compact high pressure ratio oblique flow-centrifugal combined compressor structure, is applicable to high-performance Small Aeroengine; It comprises inclined flow air compressor and centrifugal compressor two-stage, the first order is inclined flow air compressor, the second level is centrifugal compressor, one section of " S " type elbow connecting structure is adopted between inclined flow air compressor and centrifugal compressor, the bend pipe import of " S " type and inclined flow air compressor export affixed, and outlet is affixed with centrifugal compressor import.
Described oblique flow-centrifugal combined compressor structure, with blade in " S " type bend pipe described in it, and " S " type bend pipe inlet diameter is greater than " S " type winding pipe exit diameter, the area of " S " type bend pipe passage experienced by the process first increasing and reduce afterwards, to ensure flowing state good in " S " type bend pipe.
Described oblique flow-centrifugal combined compressor structure, in " S " type bend pipe described in it with blade, circumferentially be provided with in " S " type bend pipe inlet the wedge shape straightener blade that a row has 45 ° ~ 60 ° of established angles, circumferentially be provided with the return channel blade with 25 ° ~ 40 ° of established angles that a row extends towards radial direction in outlet port, two row's vane inlet all align with the exit flow direction of upstream blade simultaneously.
Described oblique flow-centrifugal combined compressor structure, the return channel blade in " S " type bend pipe described in it, can have 45 ~ 75 ° of air-flows of prewhirling by diagonal flow rotor outlet and be rectified into centrifugal impeller import and have 15 ~ 0 ° of air-flows of prewhirling.
Described oblique flow-centrifugal combined compressor structure, described in it, oblique flow level pressure ratio is 4.0-6.0: 1, and centrifugal level pressure ratio is 2.0-3.0: 1.
Described inclined flow air compressor and centrifugal compressor structure, " S " type bend pipe of a novel structure is adopted to be connected described in it between inclined flow air compressor with centrifugal compressor, compared with the two stage centrifugal gas compressor with same design parameter, its radial dimension can reduce 25%, and structure is compacter.
Described oblique flow-centrifugal combined compressor structure, strain formation rigid unitary vertically by center pull rod between the diagonal impeller of inclined flow air compressor described in it and the centrifugal impeller of centrifugal compressor, diagonal impeller and centrifugal impeller are arranged on the same axis; During work, turbine, by circular arc end tooth torsion pass, drives diagonal impeller to rotate around engine axis together with centrifugal impeller.
The invention has the beneficial effects as follows:
(1) the single-stage pressure ratio of inclined flow air compressor is higher, and earlier stages adopts inclined flow air compressor to replace multi stage axial flow compressor and makes gas compressor component number greatly few, simple and compact for structure, obviously reduce processing, install and maintenance cost;
(2) earlier stages adopts inclined flow air compressor to replace multi stage axial flow compressor and shortens supporting span, reduces shafting design difficulty;
(3) oblique flow that earlier stages adopts wide string to design distortion tolerance of calming the anger is high, and anti-foreign object strike ability (FOD) is strong, and to gap and blade surface degree of finish insensitive;
(4) oblique flow-centrifugal combined compressor stable operation range is broad, can save air-intake guide vane, complicated propeller regulating mechanism and corresponding control system;
(5) compared to two stage centrifugal air compressor structure layout, earlier stages adopts inclined flow air compressor can overcome the little restriction of two stage centrifugal gas compressor flow; Meanwhile, adopt the S type bend pipe of novel structure to be connected between inclined flow air compressor with centrifugal compressor, this avoids on the one hand the large problem of radial dimension existing for two stage centrifugal gas compressor, reduces the power acted on bearing on the other hand, adds the life-span of bearing.
Accompanying drawing explanation
Fig. 1 is ultra-compact high pressure ratio oblique flow of the present invention-centrifugal combined compressor structural representation; Wherein:
Diagonal impeller dish 1 internal wall member 2 internal wall member 3
Centrifugal impeller dish 4 center pull rod 5 axis 6
Diagonal flow rotor blade 7 circular arc end tooth 8 straightener blade 9
Wall part 10 return channel blade 11 wall part 12
Wall part 13 centrifugal rotor blade 14 radial diffuser blade 15
Axial diffuser vane 16
Embodiment
See Fig. 1, ultra-compact high pressure ratio oblique flow of the present invention-centrifugal combined compressor structure, by diagonal impeller, with minor diameter " S " the type bend pipe of rectifier and reflux blade, centrifugal impeller, radial diffuser and axial Diffuser be totally six part compositions, wherein diagonal impeller is made up of diagonal impeller dish 1 and diagonal flow rotor blade 7, centrifugal impeller is made up of centrifugal impeller dish 4 and centrifugal rotor blade 14, be connected by ultra-compact " S " type bend pipe that one section of radial dimension is little between diagonal impeller with centrifugal impeller, " S " type elbow internal wall is made up of internal wall member 2 and internal wall member 3, bend pipe outer wall is by wall part 10, wall part 12 and wall part 13 form, bend pipe import is furnished with row's straightener blade 9, and outlet is furnished with row's return channel blade 11.Diagonal impeller and centrifugal impeller are strained vertically by center pull rod 5 and are formed rigid unitary, diagonal impeller and centrifugal impeller are arranged on the same axis, during combined compressor work, turbine to centrifugal impeller dish 4, drives diagonal impeller to rotate around engine axis 6 together with centrifugal impeller by circular arc end tooth 8 torsion pass.
Ultra-compact high pressure ratio oblique flow of the present invention-centrifugal combined compressor structure, gas compressor is total to two-stage by inclined flow air compressor and centrifugal compressor and forms, the first order is inclined flow air compressor, the second level is centrifugal compressor, minor diameter " S " the type bend pipe of a segment structure novelty is adopted to be connected between inclined flow air compressor with centrifugal compressor, during gas compressor work, air-flow introduces the working blade 7 of first order inclined flow air compressor by the convergent passage of inlet casing, after working blade 7 supercharging, flow into axial flow rectifier 9, entered the centrifugal rotor blade 14 of second level centrifugal compressor by one section of minor diameter " S " type bend pipe (band return channel blade 11) after rectification diffusion, after the further supercharging of centrifugal impeller, enter blade type radial diffuser 15, to slow down wherein supercharging, pass through axial Diffuser 16 diffusion further again, rectification, last flowing in combustion chamber.
In sum, the present invention can be directly used in aero gas turbine engine, it has that structure is simple, component are few, compact structure, reliability are high and processing maintenance cost is low etc. combines many advantages, can solve domestic existing middle-size and small-size aero gas turbine engine and adopt the problem that multi stage axial flow compressor, the radial dimension that single-stage pressure ratio is low, progression is many, weight is large, manufacture cost is high and two stage centrifugal gas compressor exists existing for axial-flow-centrifugal combined compressor are large.
Claims (5)
1. high pressure ratio oblique flow-centrifugal combined compressor structure, is applicable to Small Aeroengine; It is characterized in that: comprise inclined flow air compressor and centrifugal compressor two-stage, the first order is inclined flow air compressor, the second level is centrifugal compressor, one section of " S " type elbow connecting structure is adopted between inclined flow air compressor and centrifugal compressor, the bend pipe import of " S " type and inclined flow air compressor export affixed, and outlet is affixed with centrifugal compressor import;
Wherein, with blade in described " S " type bend pipe, and " S " type bend pipe inlet diameter is greater than " S " type winding pipe exit diameter, and the area of " S " type bend pipe passage experienced by the process first increasing and reduce afterwards, to ensure not occur flow separation in " S " type bend pipe;
In described " S " type bend pipe with blade, " S " type bend pipe inlet is circumferentially provided with the wedge shape straightener blade that a row has 45 ° ~ 60 ° of established angles, outlet port is circumferentially provided with the return channel blade with 25 ° ~ 40 ° of established angles that a row extends towards radial direction, simultaneously, the import of wedge shape straightener blade is alignd with upstream diagonal flow rotor blade exit airflow direction, and return channel vane inlet aligns with wedge shape straightener blade exit flow direction, upstream.
2. high pressure ratio oblique flow according to claim 1-centrifugal combined compressor structure, it is characterized in that: the straightener blade in described " S " type bend pipe and return channel blade diagonal flow rotor outlet can being had 45 ~ 75 ° of air-flows of prewhirling and be rectified into centrifugal impeller import there are 15 ~ 0 ° of air-flows of prewhirling.
3. high pressure ratio oblique flow according to claim 1-centrifugal combined compressor structure, is characterized in that: oblique flow level pressure ratio is 4.0-6.0:1, and centrifugal level pressure ratio is 2.0-3.0:1.
4. high pressure ratio oblique flow according to claim 1-centrifugal combined compressor structure, is characterized in that: this high pressure ratio oblique flow-centrifugal combined compressor structure is compared with the two stage centrifugal gas compressor with same design parameter, and its radial dimension can reduce 25%.
5. high pressure ratio oblique flow according to claim 1-centrifugal combined compressor structure, it is characterized in that: strain formation rigid unitary vertically by center pull rod between the diagonal impeller of described inclined flow air compressor and the centrifugal impeller of centrifugal compressor, diagonal impeller and centrifugal impeller are arranged on the same axis; During work, turbine to combined compressor, drives diagonal impeller to rotate around engine axis together with centrifugal impeller by circular arc end tooth torsion pass.
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| CN103161608B (en) * | 2013-02-07 | 2014-12-24 | 南京凌日星能源科技有限公司 | Single rotor minitype turbofan engine adopting axial flow oblique flow serial composite compressing system |
| JP2014214649A (en) * | 2013-04-24 | 2014-11-17 | トヨタ自動車株式会社 | Multistage compressor |
| CN104895841B (en) * | 2015-04-30 | 2018-03-23 | 中国科学院工程热物理研究所 | Rectifier, flow passage structure, combined compressor, aero gas turbine engine |
| CN105221463B (en) * | 2015-10-14 | 2017-10-20 | 西安交通大学 | Two-stage big flow oblique flow centrifugation combination compressor with cascade EDFA |
| CN105386998A (en) * | 2015-11-27 | 2016-03-09 | 中国航空动力机械研究所 | Returning device and double-stage combined air compressor with same |
| CN105257574A (en) * | 2015-11-27 | 2016-01-20 | 中国航空动力机械研究所 | Oblique flow and centrifugal combined compressor |
| CN106989032B (en) * | 2017-03-13 | 2022-12-06 | 南京航空航天大学 | Oblique flow-centrifugal combined compressor |
| EP3376041A1 (en) | 2017-03-15 | 2018-09-19 | Siemens Aktiengesellschaft | Return stage and radial turbo fluid energy machine |
| CN107605804B (en) * | 2017-10-31 | 2019-04-30 | 湘潭大学 | The casing of centrifugal compressor |
| CN108953232B (en) * | 2018-07-20 | 2020-01-10 | 大连海事大学 | Axial-flow compressor with static blades distributed in non-axial symmetry manner |
| CN109695580B (en) * | 2018-11-27 | 2020-09-25 | 中国科学院工程热物理研究所 | Coaxial centrifugal-oblique flow counter-rotating air compressor |
| CN109737100B (en) * | 2019-01-14 | 2024-02-02 | 中国科学院工程热物理研究所 | Combined adjusting device and method for front guide vane and vaned diffuser of exhaust |
| CN109882449A (en) * | 2019-03-22 | 2019-06-14 | 中国航发常州兰翔机械有限责任公司 | A kind of aero-engine compressor front cover |
| CN113914998B (en) * | 2021-11-04 | 2022-10-14 | 中国航发湖南动力机械研究所 | Combined compression gas turbine engine |
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| US7437877B2 (en) * | 2004-02-13 | 2008-10-21 | Honda Motor Co., Ltd. | Compressor having low-pressure and high-pressure compressor operating at optimum ratio between pressure ratios thereof and gas turbine engine adopting the same |
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| GB587150A (en) * | 1942-04-18 | 1947-04-16 | Turbo Engineering Corp | Turbine unit |
| GB2395983A (en) * | 2002-12-03 | 2004-06-09 | Rolls Royce Plc | Mixed flow compressor for gas turbine engine |
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|---|---|---|---|---|
| GB689353A (en) * | 1950-03-09 | 1953-03-25 | Lysholm Alf | Improvements in centrifugal compressors |
| US6488469B1 (en) * | 2000-10-06 | 2002-12-03 | Pratt & Whitney Canada Corp. | Mixed flow and centrifugal compressor for gas turbine engine |
| US7437877B2 (en) * | 2004-02-13 | 2008-10-21 | Honda Motor Co., Ltd. | Compressor having low-pressure and high-pressure compressor operating at optimum ratio between pressure ratios thereof and gas turbine engine adopting the same |
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