CN105627969B - A kind of engine high pressure turbine clearance value correction method - Google Patents

A kind of engine high pressure turbine clearance value correction method Download PDF

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Publication number
CN105627969B
CN105627969B CN201511015873.0A CN201511015873A CN105627969B CN 105627969 B CN105627969 B CN 105627969B CN 201511015873 A CN201511015873 A CN 201511015873A CN 105627969 B CN105627969 B CN 105627969B
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pressure turbine
circle
central coordinate
high pressure
fulcrum
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CN105627969A (en
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刘永泉
赵翀
梁海涛
付鹏哲
杨乐
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AVIC Shenyang Engine Design and Research Institute
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AVIC Shenyang Engine Design and Research Institute
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B21/00—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant
    • G01B21/16—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring distance of clearance between spaced objects

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  • General Physics & Mathematics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The invention discloses a kind of engine high pressure turbine clearance value correction method, belongs to aero-engine High Pressure Turbine Clearance measurement analysis technical field.Central coordinate of circle O of the forward and backward fulcrum of engine high pressure turbine rotor on same axis projection face is obtained first1And O2, and then determine the central coordinate of circle O at axial blade center3；Afterwards, the central coordinate of circle O of high-pressure turbine outer shroud block is obtained4, all outer shroud block jitter values are drawn relative to the central coordinate of circle O4It is circumferentially distributed, finally, by space vectorTo relative to the central coordinate of circle O4Circumferentially distributed outer shroud block jitter values carry out vector teranslation, obtain revised engine high pressure turbine clearance Distribution value.Proportional positions its center of the invention according to High Pressure Turbine Rotor center between high pressure rotor fulcrum and Relative position vector of the high-pressure turbine outer shroud center in space, rotor and stator direct path correlation are analyzed, result of calculation is more accurate and can intuitively show the circumferentially distributed situation in engine turbine gap.

Description

A kind of engine high pressure turbine clearance value correction method
Technical field
The invention belongs to aero-engine High Pressure Turbine Clearance to measure analysis technical field, and in particular to a kind of engine is high Press turbine clearance value correction method.
Background technology
Engine turbine gap refers to the distance between the blade tip of engine turbine blade outer shroud block adjacent thereto, due to The long-term operating of engine so that gap width between the two will change, in the situation of the quick acceleration, deceleration of engine Under, tip clearance changes greatly, and to improve the Performance And Reliability of modern aeroengine, domestic and international many research institutions are all Successively carry out the research in terms of tip clearance control technology, and the numerical analysis for carrying out tip clearance is therein important interior One of hold.
At present, it is to the analysis method in aero-turbine gap：Aero-engine high-pressure turbine outer shroud is measured respectively Block diameter and rotor blade tip diameter simultaneously calculate respective average, using the average value difference of stator and rotor as high-pressure turbine Gap, the offset of analytic process mesohigh turbine rotor use the forward and backward fulcrum maximum eccentricity amount of rotor, are exaggerated the inclined of rotor From situation, analysis result has differences with legitimate reading.
The content of the invention
To solve the above-mentioned problems, the present invention proposes a kind of engine high pressure turbine clearance value correction method, for true Determine and draw the gap width between any High Pressure Turbine Rotor blade and high-pressure turbine outer shroud block, according to High Pressure Turbine Rotor center Its center of proportional positions and Relative position vector of the high-pressure turbine outer shroud center in space between high pressure rotor fulcrum, will turn Son is analyzed with stator direct path correlation.Result of calculation is more accurate and can intuitively show the circumferential direction point in engine turbine gap Cloth situation.
Inventive engine High Pressure Turbine Clearance value correction method, mainly includes the following steps that：
Step 1: obtain central coordinate of circle O of the forward and backward fulcrum of engine high pressure turbine rotor on same axis projection face1 And O2；
Step 2: the axial blade center distance L1 with rotor front fulcrum respectively of measurement engine high pressure turbine rotor, And the distance L2 with rear fulcrum, and with reference to the central coordinate of circle O of the forward and backward fulcrum1And O2, calculate the axial blade center Central coordinate of circle O3；
Step 3: the gap width between all high-pressure turbine blade and high-pressure turbine outer shroud blocks is measured, and it is average to calculate it Value n1；
Step 4: obtain the central coordinate of circle O of high-pressure turbine outer shroud block4, the central coordinate of circle O of the high-pressure turbine outer shroud block4It is Refer to the central coordinate of circle that formed circle is surrounded by multiple high-pressure turbine outer shroud blocks；Draw all outer shroud block jitter values relative to The central coordinate of circle O4It is circumferentially distributed, the outer shroud block jitter values refer to any high-pressure turbine blade and high-pressure turbine outer shroud block Between gap width and the average value n1 difference；
Step 5: it is central coordinate of circle O4To central coordinate of circle O3Relative position space vector
Step 6: by step 4 relative to the central coordinate of circle O4Circumferentially distributed outer shroud block jitter values with described Space vectorTranslated, obtain revised engine high pressure turbine clearance Distribution value.
Preferably, the acquisition engine high pressure turbine rotor front fulcrum central coordinate of circle O1Or the central coordinate of circle of rear fulcrum O2The step of include：
Take front fulcrum O1With rear fulcrum O2Circumferentially direction outer race bounce, and measure it relative at the beginning of engine Front fulcrum O during the design that begins1Or rear fulcrum O2The distance between axle center；
Front fulcrum O during by any of the above-described outer race bounce point relative to engine initial designs1Or rear fulcrum O2Axis The distance between heart, with being projected respectively on vertical axis, and calculates multiple projector distances in trunnion axis, in trunnion axis and vertical axis On, corresponding projector distance is averaged respectively, as central coordinate of circle O1And O2X values and y values.
In such scheme preferably, the measurement engine high pressure turbine rotor front fulcrum central coordinate of circle O1Or rear branch The central coordinate of circle O of point2The step of further include：
By front fulcrum central coordinate of circle O1X values be arranged to 0, meanwhile, by front fulcrum central coordinate of circle O1Y values and rear fulcrum Central coordinate of circle O2Carry out equal proportion conversion.
In such scheme preferably, the front fulcrum O1Or rear fulcrum O2Outer race bounce point selection include Take front fulcrum O1Or rear fulcrum O2Circumferentially direction uniform 8 outer races bounce point.
In such scheme preferably, in the step 3, the calculation procedure of the average value n1 includes：
The distance between opposite High Pressure Turbine Rotor blade tip L3 is measured, and calculates average value
The distance between corresponding high-pressure turbine outer shroud block center L4 is measured, and calculates average value
It is describedThe opposite High Pressure Turbine Rotor blade refer to centered on turbine rotor shaft to Two rotor blades of opposite direction extension, corresponding high-pressure turbine outer shroud block refer to and the opposite high-pressure turbine Two adjacent high-pressure turbine outer shroud blocks of rotor blade.
Its center of proportional positions and high pressure whirlpool of the present invention according to High Pressure Turbine Rotor center between high pressure rotor fulcrum Relative position vector of the outer shroud center in space is taken turns, rotor and stator direct path correlation are analyzed.Result of calculation is more accurate and can Intuitively to show the circumferentially distributed situation in engine turbine gap.Effectively improve between aero-engine high-pressure turbine blade tip The precision and accuracy of the actual distribution result of gap, can instruct the assembly work of High Pressure Turbine Rotor, rationally between control blade tip Gap.
Brief description of the drawings
Fig. 1 is the flow chart according to a preferred embodiment of inventive engine High Pressure Turbine Clearance value correction method.
Fig. 2 is the front and rear fulcrum perspective view of embodiment illustrated in fig. 1.
Fig. 3 is the outer shroud block gap distribution schematic diagram that the measurement of embodiment illustrated in fig. 1 obtains.
Fig. 4 is the revised outer shroud block gap distribution schematic diagram of embodiment illustrated in fig. 1.
Embodiment
To make the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction with the embodiment of the present invention Attached drawing, the technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class As label represent same or similar element or there is same or like element.Described embodiment is the present invention Part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to uses It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people Member's all other embodiments obtained without creative efforts, belong to the scope of protection of the invention.Under Face is described in detail the embodiment of the present invention with reference to attached drawing.
In the description of the present invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear", The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outer " is based on attached drawing institutes The orientation or position relationship shown, is for only for ease of the description present invention and simplifies description, rather than instruction or the dress for implying meaning Put or element there must be specific orientation, with specific azimuth configuration and operation, therefore it is not intended that the present invention is protected The limitation of scope.
Inventive engine High Pressure Turbine Clearance value correction method, for determining and drawing any High Pressure Turbine Rotor blade With the gap width between high-pressure turbine outer shroud block, according to proportional positions of the High Pressure Turbine Rotor center between high pressure rotor fulcrum Its center and Relative position vector of the high-pressure turbine outer shroud center in space, rotor and stator direct path correlation are analyzed.Calculate knot Fruit is more accurate and can intuitively show the circumferentially distributed situation in engine turbine gap.
Inventive engine High Pressure Turbine Clearance value correction method, as shown in Figure 1, mainly including the following steps that：
Step 1: obtain central coordinate of circle O of the forward and backward fulcrum of engine high pressure turbine rotor on same axis projection face1 And O2；
Step 2: the axial blade center distance L1 with rotor front fulcrum respectively of measurement engine high pressure turbine rotor, And the distance L2 with rear fulcrum, and with reference to the central coordinate of circle O of the forward and backward fulcrum1And O2, calculate the axial blade center Central coordinate of circle O3；
Step 3: the gap width between all high-pressure turbine blade and high-pressure turbine outer shroud blocks is measured, and it is average to calculate it Value n1；
Step 4: obtain the central coordinate of circle O of high-pressure turbine outer shroud block4, the central coordinate of circle O of the high-pressure turbine outer shroud block4It is Refer to the central coordinate of circle that formed circle is surrounded by multiple high-pressure turbine outer shroud blocks；Draw all outer shroud block jitter values relative to The central coordinate of circle O4It is circumferentially distributed, the outer shroud block jitter values refer to any high-pressure turbine blade and high-pressure turbine outer shroud block Between gap width and the average value n1 difference；
Step 5: it is central coordinate of circle O4To central coordinate of circle O3Relative position space vector
Step 6: by step 4 relative to the central coordinate of circle O4Circumferentially distributed outer shroud block jitter values with described Space vectorTranslated, obtain revised engine high pressure turbine clearance Distribution value.
It should be noted that in step 1, the central coordinate of circle O on same axis projection face1And O2As shown in Fig. 2, its In, the line of front and rear fulcrum forms rotor axis, it can be seen that and itself and stator axis are there occurs deviation, in the present embodiment, Fig. 2 Shown front fulcrum perspective plane, rear fulcrum perspective plane and High Pressure Turbine Rotor blade center perspective plane is same axis projection Face, and this schematic diagram is schematic, i.e. center (the i.e. central coordinate of circle O of High Pressure Turbine Rotor blade3) be not necessarily located at before, The centre of rear fulcrum, as described in step 2, central coordinate of circle O3Need in the axial blade by engine high pressure turbine rotor The heart distance L1 with rotor front fulcrum respectively, and calculated with the distance L2 of rear fulcrum, specifically, according to mathematical relationship Equal proportion relation in formula is determined, and in general, actual measurement High Pressure Turbine Rotor blade axial centre is in high pressure rotor branch Proportional positions between point, it is 0.812 to determine proportionality coefficient, and the present embodiment does not repeat.
In the present embodiment, for convenience, by front fulcrum central coordinate of circle O1X values be arranged to 0, meanwhile, by front fulcrum Central coordinate of circle O1Y values and rear fulcrum central coordinate of circle O2Carry out equal proportion conversion, that is to say, that by central coordinate of circle O1One value It is set as 0, in other words, by central coordinate of circle O1It is scheduled in reference axis, it is convenient to calculate.
It is understood that why not by central coordinate of circle O1Be positioned at origin position, be because the present embodiment in, it is right Front fulcrum central coordinate of circle O1Or the central coordinate of circle O of rear fulcrum2Value determined by outer race bounce, here, in the present embodiment Front fulcrum during using engine initial designs is as origin, then after engine operates a period of time, it beats position will not One is positioned at origin.
Specifically, the present embodiment front fulcrum O1Or rear fulcrum O2Outer race bounce point choosing method include take preceding branch Point O1Or rear fulcrum O2Circumferentially direction uniform 8 outer races bounce point.To each outer shroud bounce point, it is measured Front fulcrum O during relative to engine initial designs1Or rear fulcrum O2The distance between axle center, and then by any of the above-described bearing Front fulcrum O when outer shroud bounce point is relative to engine initial designs1Or rear fulcrum O2The distance between axle center in trunnion axis With being projected respectively on vertical axis, and calculate multiple projector distances, on trunnion axis and vertical axis, respectively by corresponding projection away from From being averaged, as central coordinate of circle O1And O2X values and y values, specific signal is as shown in table 1.
Table 1
By taking front fulcrum as an example, using 12 directions as starting point, eight points are chosen clockwise and are measured, each puts it in x A value is projected on axis (or y-axis), for example the 4th point is the point in fourth quadrant in coordinate system, it is 45 ° of x-axis partial below, The point is given in table 1 apart from origin -0.02mm, the 5th point is the point in negative direction in y-axis for another example, its value is -0.02, that 5th point its be projected as 0 in x-axis, its on the y axis be projected as -0.02.
By above-mentioned 8 bounce points, take the average value projected in x-axis and take the average value projected in y-axis, be the center of circle Coordinate O1, in the present embodiment, the value of x, y that Fig. 1 is provided are by central coordinate of circle O1X values be arranged to conversion value after 0.
Afterwards, it is necessary to measure the gap width between all high-pressure turbine blade and high-pressure turbine outer shroud blocks, and it is flat to calculate it Average n1, the calculation procedure of the average value n1 include：
The distance between opposite High Pressure Turbine Rotor blade tip L3 is measured, and calculates average value
The distance between corresponding high-pressure turbine outer shroud block center L4 is measured, and calculates average value
It is describedThe opposite High Pressure Turbine Rotor blade refer to centered on turbine rotor shaft to Two rotor blades of opposite direction extension, corresponding high-pressure turbine outer shroud block refer to and the opposite high-pressure turbine Two adjacent high-pressure turbine outer shroud blocks of rotor blade.
And then the central coordinate of circle O of high-pressure turbine outer shroud block can be obtained4, the central coordinate of circle O of the high-pressure turbine outer shroud block4 Refer to the central coordinate of circle that formed circle is surrounded by multiple high-pressure turbine outer shroud blocks；It is opposite to draw all outer shroud block jitter values In the central coordinate of circle O4It is circumferentially distributed, the outer shroud block jitter values refer to any high-pressure turbine blade and high-pressure turbine outer shroud The difference of gap width and the average value n1 between block.As shown in Fig. 3, the present embodiment, which takes, counts out as 150, such as its In eight jitter values for shown in table 2.
2 high-pressure turbine outer shroud block jitter values of table
High-pressure turbine outer shroud block 1 2 3 4 5 6 7 8
Jitter values 0 0.02 -0.03 0.07 0.04 -0.02 0.01 -0.02
It is central coordinate of circle O4To central coordinate of circle O3Relative position space vectorReferring again to Fig. 1, by the vector Vector teranslation is carried out in figure 3, and forms the relation schematic diagram in Fig. 4, it is necessary to illustrate, in Fig. 4, with central coordinate of circle O4For Coordinate origin, inner circle are gap minimum value schematic diagram, and cylindrical is spacing maxima schematic diagram, and middle irregular circle is the present invention Finally formed High Pressure Turbine Clearance value distinguishes schematic diagram, i.e., finally obtains the actual distribution situation of high-pressure turbine tip clearance. It is clear that the outer shroud block of the top of high-pressure turbine is serious with blade wear from figure, gap is more intuitively shown It is worth circumferentially distributed characteristic.
Its center of proportional positions and high pressure whirlpool of the present invention according to High Pressure Turbine Rotor center between high pressure rotor fulcrum Relative position vector of the outer shroud center in space is taken turns, rotor and stator direct path correlation are analyzed.Result of calculation is more accurate and can Intuitively to show the circumferentially distributed situation in engine turbine gap.Effectively improve between aero-engine high-pressure turbine blade tip The precision and accuracy of the actual distribution result of gap, can instruct the assembly work of High Pressure Turbine Rotor, rationally between control blade tip Gap.
It is last it is to be noted that：The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent Pipe is with reference to the foregoing embodiments described in detail the present invention, it will be understood by those of ordinary skill in the art that：It is still It can modify to the technical solution described in foregoing embodiments, or which part technical characteristic is equally replaced Change；And these modifications or replacement, the essence of appropriate technical solution is departed from the essence of various embodiments of the present invention technical solution God and scope.

Claims (5)

  1. A kind of 1. engine high pressure turbine clearance value correction method, for determining and drawing any High Pressure Turbine Rotor blade and height Press the gap width between turbine outer ring block, it is characterised in that including：
    Step 1: obtain central coordinate of circle O of the forward and backward fulcrum of engine high pressure turbine rotor on same axis projection face1And O2；
    Step 2: the axial blade center distance L1 with rotor front fulcrum respectively of measurement engine high pressure turbine rotor, and With the distance L2 of rear fulcrum, and with reference to the central coordinate of circle O of the forward and backward fulcrum1And O2, calculate the circle at the axial blade center Heart coordinate O3；
    Step 3: measuring the gap width between all high-pressure turbine blade and high-pressure turbine outer shroud blocks, and calculate its average value n1；
    Step 4: obtain the central coordinate of circle O of high-pressure turbine outer shroud block4, the central coordinate of circle O of the high-pressure turbine outer shroud block4Refer to by Multiple high-pressure turbine outer shroud blocks surround the central coordinate of circle of formed circle；All outer shroud block jitter values are drawn relative to described Central coordinate of circle O4It is circumferentially distributed, the outer shroud block jitter values refer between any high-pressure turbine blade and high-pressure turbine outer shroud block Gap width and the average value n1 difference；
    Step 5: it is central coordinate of circle O4To central coordinate of circle O3Relative position space vector
    Step 6: by step 4 relative to the central coordinate of circle O4Circumferentially distributed outer shroud block jitter values with the space VectorTranslated, obtain revised engine high pressure turbine clearance Distribution value.
  2. 2. engine high pressure turbine clearance value correction method as claimed in claim 1, it is characterised in that the acquisition engine High Pressure Turbine Rotor front fulcrum central coordinate of circle O1Or the central coordinate of circle O of rear fulcrum2The step of include：
    Take front fulcrum O1With rear fulcrum O2Circumferentially direction outer race bounce, and measure it and initially set relative to engine The front fulcrum O of timing1Or rear fulcrum O2The distance between axle center；
    Front fulcrum O during by any of the above-described outer race bounce point relative to engine initial designs1Or rear fulcrum O2Axle center it Between distance in trunnion axis with being projected respectively on vertical axis, and calculate multiple projector distances, on trunnion axis and vertical axis, point Corresponding projector distance is not averaged, as central coordinate of circle O1And O2X values and y values.
  3. 3. engine high pressure turbine clearance value correction method as claimed in claim 2, it is characterised in that the measurement engine High Pressure Turbine Rotor front fulcrum central coordinate of circle O1Or the central coordinate of circle O of rear fulcrum2The step of further include：
    By front fulcrum central coordinate of circle O1X values be arranged to 0, meanwhile, by front fulcrum central coordinate of circle O1Y values and rear fulcrum the center of circle Coordinate O2Carry out equal proportion conversion.
  4. 4. engine high pressure turbine clearance value correction method as claimed in claim 2, it is characterised in that the front fulcrum O1Or Rear fulcrum O2Outer race bounce point selection include take front fulcrum O1Or rear fulcrum O2Uniform 8 of circumferentially direction Outer race bounce point.
  5. 5. engine high pressure turbine clearance value correction method as claimed in claim 1, it is characterised in that in the step 3 In, the calculation procedure of the average value n1 includes：
    The distance between opposite High Pressure Turbine Rotor blade tip L3 is measured, and calculates average value
    The distance between corresponding high-pressure turbine outer shroud block center L4 is measured, and calculates average value
    It is describedThe opposite High Pressure Turbine Rotor blade refers to centered on turbine rotor shaft to opposite Direction extension two rotor blades, corresponding high-pressure turbine outer shroud block refers to and the opposite High Pressure Turbine Rotor Two adjacent high-pressure turbine outer shroud blocks of blade.
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Publication number Priority date Publication date Assignee Title
US11307015B2 (en) 2018-09-12 2022-04-19 Dalian University Of Technology Method for calculating eccentricity of rotor assembly axis based on radial runout measurement
CN109117461B (en) * 2018-09-12 2021-08-20 大连理工大学 Method for calculating rotor assembly axis eccentricity based on radial run-out measurement
CN109556556B (en) * 2018-12-18 2022-02-22 中国航发沈阳发动机研究所 Method for measuring blade tip clearance of high-pressure turbine rotor stator in cold-state assembly process
CN115235404B (en) * 2022-09-22 2022-12-06 中国航发燃气轮机有限公司 Rotor and stator clearance correction method for heavy gas turbine

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10352790B4 (en) * 2003-11-12 2006-12-28 Mtu Aero Engines Gmbh Method for determining and / or analyzing and / or designing columns, in particular of a turbomachine
CN104075677A (en) * 2014-06-30 2014-10-01 东北大学 Method and system for measuring concentricity and tip clearance of rotor and stator of aero-engine
CN104165069A (en) * 2013-05-15 2014-11-26 通用电气公司 Modified turbine buckets and methods for modifying turbine buckets
EP2882078A1 (en) * 2013-12-05 2015-06-10 Siemens Aktiengesellschaft Electrical machine with a permanent magnet and a coil

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10352790B4 (en) * 2003-11-12 2006-12-28 Mtu Aero Engines Gmbh Method for determining and / or analyzing and / or designing columns, in particular of a turbomachine
CN104165069A (en) * 2013-05-15 2014-11-26 通用电气公司 Modified turbine buckets and methods for modifying turbine buckets
EP2882078A1 (en) * 2013-12-05 2015-06-10 Siemens Aktiengesellschaft Electrical machine with a permanent magnet and a coil
CN104075677A (en) * 2014-06-30 2014-10-01 东北大学 Method and system for measuring concentricity and tip clearance of rotor and stator of aero-engine

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
涡轮叶尖间隙动态建模的LS-SVM方法;贾丙辉，张小栋，侯育军;《计算机仿真》;20120430;第29卷(第4期);95-101 *
考虑主动间隙控制的涡轮叶尖间隙建模计算研究;周骁，张海波，王继强，宁景涛;《推进技术》;20150731;第36卷(第7期);1093-1102 *

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