CN105317559B - With support case after the turbine of rectification leaf grating integration connection - Google Patents
With support case after the turbine of rectification leaf grating integration connection Download PDFInfo
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- CN105317559B CN105317559B CN201410234579.8A CN201410234579A CN105317559B CN 105317559 B CN105317559 B CN 105317559B CN 201410234579 A CN201410234579 A CN 201410234579A CN 105317559 B CN105317559 B CN 105317559B
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- blade
- support case
- turbine
- inframarginal
- plate
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Abstract
Support case portion profile is identical with support case after conventional turbine after support case and the attachment structure of rectification leaf grating integration, its turbine after turbine.Its difference and it is characterised by：It is to the addition of straightener(stator) blade structure between the outer shroud of support case, inner ring and support plate after conventional turbine, and wherein blade construction includes；Blade supramarginal plate, blade, blade flow guidance tape, blade inframarginal and blade inframarginal front end baffle.Blade supramarginal plate is fixed on support case outer shroud by radial screw, and blade inframarginal rear end is positioned on support case inner ring aft end flange by special radial bolts axial and circumferential；Gas channel is formed between blade flow guidance tape, blade, blade supramarginal plate and load support plate.The present invention realizes support case and the integration of rectification leaf grating after turbine on the premise of support case intensity, compatibility of deformation and support stiffness after not changing support case structure after turbine significantly, not influenceing.
Description
Technical field
The present invention relates to support case after a kind of turbine and the attachment structure of rectification leaf grating integration, belong to aero propulsion skill
Art field.
Background technology
On currently advanced aero gas turbine engine, afterbunring is installed generally between turbine and jet pipe
Room, carries out reheat augmentation, continues to increase thrust after engine reaches thrust maximum rating.And low-pressure turbine exit air-flow is usual
Requirement of the after-burner for low-pressure turbine exit flow angle can not be met, so in Low Pressure Turbine Rotor and after-burner
Between need to install straightener(stator) blade additional, to air-flow carry out rectification.
Above-mentioned this design will cause rear support case to be moved rearward to install extra outlet straightener(stator) blade, so that
Make the increase of rotor axial length, bearing supporting span is increased.Turbine part quantity can be increased accordingly, cause engine weight to increase
Plus, it is unfavorable for improving engine thrust-weight ratio.
Pu Hui companies of the U.S. are when designing PW4000 h type engine hs, by the load branch in rear support case (as shown in Figure 1)
Plate Cross section Design can carry out rectification directly through combustion gas stream into blade profile, load support plate using load support plate.But this support plate is done
Form into blade profile has more defect, such as the support stiffness requirement of rear support case limits the number of load support plate, still
Need enough numbers of blade again to reach good rectification effect at pneumatic aspect.
The content of the invention
In order to overcome the above mentioned problem of prior art, the invention provides support case after a kind of turbine and rectification leaf grating one
Body attachment structure, the structure is not substantially changing after turbine in the case of support case stress, deformation and support stiffness, can
Rectification cascade structure and rear support case are attached positioning.
In the rear support case and rectification leaf grating integrated programme according to the present invention, by support case after turbine and turbine
Final stage straightening vane is designed to the structure of integration, can not only so meet after-burner for low-pressure turbine exit flow angle
Requirement, may also reach up shorten low pressure rotor axial length, mitigate weight and reduce number of parts purpose, so as to improve
Engine thrust-weight ratio.
With conventional rectifier cascade structure differently, according to an aspect of the present invention, needed for integral structure Leaf
Circumferentially to be dispersedly distributed between rear support case each support plate, and avoid rectification cascade structure to rear support case intensity
The requirement of excessive influence is produced with radial rigidity, blade upper limb is employed and fixes, " the cantilever that lower edge is only fixed along the axial and circumferential directions
Formula " blade fixing structure.
The advantage of the present invention compared with prior art is：
(1) rectification cascade structure is with the addition of, without being had a significant effect to support case intensity and support stiffness after original；
(2) rectification cascade structure is with the addition of, the compatibility of deformation without influenceing original rear support case；
(3) rectification cascade structure is with the addition of, without significantly changing original rear support case structure；
(4) weight of turbine part is reduced, the axial length of turbine rotor is shortened, improves thrust-weight ratio, improve
The performance of whole aero-engine.
According to an aspect of the invention, there is provided a kind of have after the turbine with the integrated attachment structure of rectification leaf grating
Support case, it is characterised in that including：Support case outer shroud afterwards；Support case inner ring afterwards；Load support plate；Circumferentially discretely pacify
Straightener(stator) blade structure between each load support plate and between outer shroud and inner ring.
Brief description of the drawings
Fig. 1 is support case after Pu Hui companies PW4000 engines；
Fig. 2 is along blade section figure according to the integral structure of one embodiment of the present of invention；
For the integral structure schematic three dimensional views according to one embodiment of the present of invention, (1/N models, N is load support plate to Fig. 3
Number)；
Fig. 4 A and Fig. 4 B are the radial bolts structure and assembling schematic diagram according to one embodiment of the present of invention.
Label declaration in figure：
1-radial screw；2-rear support case outer shroud；3-blade supramarginal plate；
4-blade；5-blade flow guidance tape；6-blade inframarginal；
7-radial bolts；8-rear support case inner ring aft end flange；
9-rear support case inner ring；10-blade inframarginal front apron；
11-rear support case load support plate；
12-self-locking nut；13-radial bolts cylindrical portion；
14-radial bolts cylindrical portion bottom surface；
15-radial bolts threaded portion.
Embodiment
The invention provides the integrated attachment structure of support case after a kind of turbine and rectification leaf grating, below in conjunction with the accompanying drawings and
The present invention is further illustrated for embodiment.
As shown in Figures 2 and 3, support case and rectification leaf grating one after turbine according to an embodiment of the invention
Change in attachment structure, except in the rear support case outer shroud 2 included by support case structure after existing turbine, rear support case
Outside ring 9 and load support plate 11, blade 4 is circumferentially discretely arranged between each load support plate 11, cascade structure includes
Blade supramarginal plate 3, blade 4, blade passage 5 and blade inframarginal 6.
Screwed hole, the corresponding position opened hole of rear support case outer shroud 2 are opened at blade supramarginal plate 3 respectively, using radially
Blade supramarginal plate 3 is fully connected by screw 1 to be fixed on rear support case outer shroud 2；In the leading portion of blade inframarginal 6, baffle plate knot is set
Structure 10, and do integral, limit axial displacement of the lower end of blade 4 under Aerodynamic force action；After rear support case inner ring 9
End sets flange 8, is attached the rear end of blade inframarginal 6 and flange 8 using a kind of special radial bolts structure.
As shown in Figure 4 A and 4 B shown in FIG., it is above-mentioned radial bolts structure and its assembling schematic diagram；Wherein, respectively under blade
The rear end of listrium 6 and the correspondence position opened hole of rear support case inner ring aft end flange 8, wherein the through-hole aperture R1 on inframarginal 6
More than the through-hole aperture R2 on flange 8.Radial bolts 7 are processed making as follows：With plain bolt differently, spiral shell
Bolt 7 (see Fig. 4 B) includes the cylindrical portion 13 of upper end and the threaded portion 15 of lower end, and the diameter D1 of cylindrical portion 13 is more than threaded portion 15
Big footpath D2, diameter Relationship meets R1>D1>R2>D2.When assembling is installed, by the through hole of blade inframarginal 6 and rear support case 9
Inner ring aft end flange 8 on through hole alignment after, the bolt 7 is radially from top to bottom passed through, according to diameter Relationship R1>D1>
R2>D2, bolt cylindrical portion 13 will not pass through the through hole on flange 8.Assembled using self-locking nut 12, utilize bolt cylinder
Bolt 7 is fixed on support case flange 8 by portion bottom surface 14 and self-locking nut 12.This bolt arrangement only constrains blade lower edge
The axial and circumferential displacement of plate 6, but blade inframarginal 6 can along bolt 7 center line, i.e., certain RADIAL of support case after turbine
Freely activity.
Present inventor has performed the Strength co-mputation of rear support case, rear support case high-temperature fuel gas heat after turbine is calculated
Intensity and deformation under load.Wherein, ANSYS finite element analysis softwares are make use of, the week of 1/N (N is load support plate number) is used
Phase Cyclic Symmetry model, passes through the convection transfer rate meter of support case after addition and blade surface radially different zones first
Calculate and simulate its operating temperature, afterwards by the way of thermosetting coupling, using the temperature field as the temperature boundary condition of model, and
Axial constraint is added on rear support case outer race front face and is used as displacement boundary conditions.Between its Leaf and rear support case
Mode of the relative restraint according to described in invention is added, the relatively rear support case outer shroud addition staff cultivation of blade supramarginal plate, under
The relatively rear support case addition axial and circumferential constraint in listrium rear end, radial screw and the fixed work of radial bolts are simulated with this
With.Strength Calculation is carried out to rear support case.Original rear support case Strength co-mputation is shown, at load support plate
Temperature apparently higher than inner and outer ring, it is main stress producing cause that thermal expansion amount difference, which causes thermal deformation uncoordinated,.In book
In the structure of invention, the design of cantilever is used to rectification leaf grating, the thermal expansion system due to leaf grating material can be reduced to greatest extent
Number causes further thermal deformation problem of disharmony different from the thermal coefficient of expansion of synthermal lower rear support case material, so
Stress will not be caused further to increase.The Strength co-mputation that the present invention is carried out shows, using the integration connection positioning side of the present invention
Formula, the maximum radial stress of integral structure is almost unchanged relative to rear support case, and maximum radial stress is added
4.25%.
In the present inventor is calculated the support stiffness of rear support case, support case is in bearing load after main investigation
Deformation under effect, its supporting is calculated by the radial displacement difference of support case inner and outer ring radial direction correspondence position after calculating firm
Degree.Wherein, using full model, the same Strength co-mputation of relative restraint between blade and rear support case.In rear support case outer shroud
Front end face adds some addition axial constraint, and in rear support case inner ring lower half circle directly over axial constraint, outer race front face
Ring adds the unit force of Sine distribution to simulate bearing load.As a result show, using the integrated attachment structure of the present invention, supporting
Rigidity averagely adds 1.545% in each circumferential position.Due to only using footpath at support case outer shroud and blade supramarginal plate
To being connected, and axial and circumferential displacement is only limited at support case inner ring and blade inframarginal, so adding rectification leaf grating
Afterwards, integrally-built supporting radial rigidity is basically unchanged.
It is described above, it is only part embodiment of the present invention, but protection scope of the present invention is not limited thereto, times
What those skilled in the art the invention discloses technical scope in, the change or replacement that can be readily occurred in should all be covered
Within protection scope of the present invention.
Claims (5)
1. a kind of have support case after the turbine with the integrated attachment structure of rectification leaf grating, it is characterised in that including：
Support case outer shroud (2) afterwards；
Support case inner ring (9) afterwards；
Load support plate (11)；
Circumferentially discretely it is arranged between each load support plate (11) and the straightener(stator) blade between outer shroud (2) and inner ring (9)
Structure,
Wherein：
The straightener(stator) blade structure includes blade supramarginal plate (3), blade (4), blade flow guidance tape (5), blade inframarginal (6) and leaf
Piece inframarginal front end baffle (10)；
Support case has cascade structure after the turbine, and the cascade structure includes blade supramarginal plate (3), blade (4), blade flow
Guidance tape (5) and blade inframarginal (6).
2. support case after turbine according to claim 1, it is characterised in that：
Axial and circumferential of the rear end of blade inframarginal (6) by radial bolts (7) along support case after turbine, which are positioned at, to be held
On the aft end flange (8) of power casing inner ring (9)；
Gas channel is formed between blade flow guidance tape (5), blade (4), blade supramarginal plate (3) and load support plate (11).
3. support case after turbine according to claim 2, it is characterised in that：
Blade supramarginal plate (3) is fixed on support case outer shroud (2) by radial screw (1), and radial bolts (7) only carry out axle
To the positioning with circumference.
4. support case after turbine according to claim 2, it is characterised in that：
Blade supramarginal plate (3) is fixed on support case outer shroud (2) by radial screw (1),
Had on the correspondence position of the rear end of blade inframarginal (6) and the aft end flange (8) of rear support case inner ring (9)
Through-hole aperture R1 on through hole, its Leaf inframarginal (6) is more than the through-hole aperture R2 on aft end flange (8),
In the state of by the through hole alignment on the through hole of blade inframarginal (6) and aft end flange (8), radial bolts (7) edge
The radial direction of support case is passed through from outside to inside after turbine,
Radial bolts (7) include the cylindrical portion (13) of upper end and the threaded portion (15) of lower end, and the diameter D1 of cylindrical portion (13) is more than
The big footpath D2 of threaded portion (15), diameter Relationship is met
R1>D1>R2>D2,
Because this relation, cylindrical portion (13) cannot pass through the through hole on aft end flange (8) when assembling is installed.
5. support case after turbine according to claim 4, it is characterised in that：
Assembled using self-locking nut (12), make bolt (7) using the bottom surface (14) and self-locking nut (12) of cylindrical portion (13)
It is fixed on aft end flange (8),
So as to only prohibit the axial and circumferential displacement of blade inframarginal (6), but blade inframarginal (6) can be along along bolt (7)
Heart line is the RADIAL movement of support case after turbine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410234579.8A CN105317559B (en) | 2014-05-29 | 2014-05-29 | With support case after the turbine of rectification leaf grating integration connection |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410234579.8A CN105317559B (en) | 2014-05-29 | 2014-05-29 | With support case after the turbine of rectification leaf grating integration connection |
Publications (2)
| Publication Number | Publication Date |
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| CN105317559A CN105317559A (en) | 2016-02-10 |
| CN105317559B true CN105317559B (en) | 2017-08-04 |
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| CN201410234579.8A Expired - Fee Related CN105317559B (en) | 2014-05-29 | 2014-05-29 | With support case after the turbine of rectification leaf grating integration connection |
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| CN107605604B (en) * | 2017-09-15 | 2019-04-16 | 中国科学院工程热物理研究所 | It is a kind of be suitable for the non-coordinating thermal deformation of inner and outer ring casing obturage and auxiliary location structure |
| CN107476885B (en) * | 2017-09-15 | 2019-12-20 | 中国科学院工程热物理研究所 | Structure capable of realizing coordinated deformation of inner ring casing and outer ring casing in high-temperature environment |
| CN111219251B (en) * | 2018-11-26 | 2021-05-04 | 中国航发商用航空发动机有限责任公司 | Rear bearing frame of aero-engine |
| CN110196167B (en) * | 2019-06-14 | 2021-01-08 | 中国航发沈阳发动机研究所 | Core machine test rear casing |
| CN110469409B (en) * | 2019-08-30 | 2021-09-28 | 中国航发动力股份有限公司 | Assembly method based on flexible connection structure assembly |
| CN110617115B (en) * | 2019-10-29 | 2021-11-02 | 北京动力机械研究所 | Turbine engine guide ring assembly produced by additive manufacturing mode |
| CN111852581A (en) * | 2020-07-24 | 2020-10-30 | 中国科学院工程热物理研究所 | Supporting plate structure suitable for main force bearing casing force transmission |
| CN112253262B (en) * | 2020-10-21 | 2022-11-22 | 中国航发沈阳发动机研究所 | Integrated form fuel feeding bleed structure |
| CN112392564A (en) * | 2020-11-13 | 2021-02-23 | 中国航发沈阳发动机研究所 | Connection structure of outer loop machine casket and radials |
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| CN101858229A (en) * | 2010-04-29 | 2010-10-13 | 中国燃气涡轮研究院 | Engine hot-centering and force-bearing type guider |
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| US4016718A (en) * | 1975-07-21 | 1977-04-12 | United Technologies Corporation | Gas turbine engine having an improved transition duct support |
| WO2013140655A1 (en) * | 2012-03-19 | 2013-09-26 | 三菱重工業株式会社 | Gas turbine |
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| CN105317559A (en) | 2016-02-10 |
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Granted publication date: 20170804 Termination date: 20190529 |