CN108691583A - Casing among turbogenerator - Google Patents
Casing among turbogenerator Download PDFInfo
- Publication number
- CN108691583A CN108691583A CN201710228722.6A CN201710228722A CN108691583A CN 108691583 A CN108691583 A CN 108691583A CN 201710228722 A CN201710228722 A CN 201710228722A CN 108691583 A CN108691583 A CN 108691583A
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- CN
- China
- Prior art keywords
- casing
- inner ring
- outer shroud
- hole
- flow
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/26—Double casings; Measures against temperature strain in casings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The present invention relates to turbogenerator technical fields, more particularly to casing among a kind of turbogenerator, including:Casing outer shroud and casing inner ring, casing outer shroud are set in outside casing inner ring, and the longitudinal center line of casing outer shroud, the longitudinal center line of casing inner ring are overlapped with the axis of engine shaft, have interval between casing outer shroud and casing inner ring;Multiple guide vanes are provided between casing outer shroud and casing inner ring, multiple guide vanes are circumferentially uniformly distributed around the axis of engine shaft, the direction for guiding air-flow.Casing among turbogenerator provided by the invention, by the way that guide vane is arranged, it being capable of correct guidance air-flow, reduce aerodynamic loss so that intermediate casing is integrated with the effect of nozzle ring, and air-flow is guided without in addition setting nozzle ring, so as to reduce engine component, so that engine part quantity and engine weight is reduced, while keeping engine arrangement compacter, shortens engine entire length.
Description
Technical field
The present invention relates to turbogenerator technical fields, more particularly to casing among a kind of turbogenerator.
Background technology
Casing is one of important part of aero-engine, it is the pedestal of entire engine, is in aero-engine
Main load component, contour structures are complicated, and different engines, engine different parts, casing shape is different, machine
The function of casket part determines the shape of casing, but their essential characteristic is the shell and support plate composition of cylindrical shape or cone
Component, since casing Element Design difficulty is big, the period is long, and in the design of entire engine, the design of casing accounts for quite big
Proportion, the design efficiency for improving casing is designed with important meaning to compression engine complete machine.
As turboshaft engine middle section, intermediate supports casing is located at after gas-turbine blade outlet, and freely
Before nozzle ring entrance.Hollow support blade can be arranged for lubrication in traditional intermediate casing while playing a supporting role
Oil circuit passes through, but needs in addition to be arranged nozzle ring with correct guidance air-flow, so that engine part quantity and hair
Motivation weight increases, while also increasing motor length.How in the supporting role for ensureing intermediate casing and guarantee lubricating oil
Correct guidance air-flow becomes problem while road is arranged.
Invention content
Based on this, it is necessary to which the problems such as having a single function, can not being oriented to air-flow for traditional intermediate casing provides one kind
It is integrated with casing among the turbogenerator of ir-flow guide function.
Above-mentioned purpose is achieved through the following technical solutions:
A kind of turbogenerator centre casing, including casing outer shroud and casing inner ring, casing outer shroud are set in casing inner ring
Outside, the longitudinal center line of casing outer shroud, casing inner ring longitudinal center line overlapped with the axis of engine shaft, casing outer shroud with
There is interval between casing inner ring;
Multiple guide vanes, axis of multiple guide vanes around engine shaft are provided between casing outer shroud and casing inner ring
Line is circumferentially uniformly distributed, the direction for guiding air-flow.
One end of each guide vane is all connected with casing outer shroud in one of the embodiments, and the other end is all connected with casing
Inner ring, and the leading edge of guide vane and trailing edge are formed by the angled setting of axis of plane and engine shaft, make air-flow into
The outflow direction for entering direction and air-flow forms angle.
The axis side of the approach axis and engine shaft of the air-flow of the edge of guide vane in one of the embodiments,
To angular range be 20 °~70 °;The axis direction for flowing out direction and engine shaft of air-flow at the trailing edge of guide vane
Angular range is 50 °~90 °.
Casing outer shroud is connect with casing inner ring by multiple support blades in one of the embodiments,;Multiple support leaves
Piece is circumferentially uniformly distributed around the axis of engine shaft, and one end of each support blade connects casing outer shroud, and the other end connects machine
Casket inner ring.
The vane hole through both ends is both provided in each support blade in one of the embodiments, for for lubrication
Oil pipe passes through;It is respectively arranged with the first through hole being connected to vane hole and the second through-hole on casing outer shroud, casing inner ring.
The cross sectional shape of vane hole is adapted with the cross sectional shape of support blade in one of the embodiments,.
Each support blade is the hollow housing of both ends open in one of the embodiments, and hollow space is formed
Vane hole;The shape of first through hole, the shape of the second through-hole are consistent with the cross sectional shape of vane hole.
In one of the embodiments, along the direction of the leading edge of support blade to trailing edge, the cross-sectional width of vane hole
Numberical range is 8mm-20mm.
The blade profile of support blade and the blade profile of guide vane are consistent in one of the embodiments,.
Casing among above-mentioned turbogenerator, by the way that guide vane is arranged, can correct guidance air-flow, reduce pneumatic damage
It losing so that intermediate casing is integrated with the effect of nozzle ring, and air-flow is guided without in addition setting nozzle ring, so as to
Engine component is reduced, so that engine part quantity and engine weight is reduced, while keeping engine arrangement compacter, is contracted
Short engine entire length.
Description of the drawings
Fig. 1 is the structural blast schematic diagram of casing among turbogenerator provided in an embodiment of the present invention;
Fig. 2 is the structural schematic diagram of casing among turbogenerator provided in an embodiment of the present invention;
Fig. 3 is the side view of casing among turbogenerator provided in an embodiment of the present invention;
Fig. 4 is the schematic cross-section of the guide vane of casing among turbogenerator provided in an embodiment of the present invention;
Fig. 5 is the schematic cross-section of the support blade of casing among turbogenerator provided in an embodiment of the present invention.
Wherein:
100- casing outer shrouds;
110- first through hole;
200- casing inner ring;
The second through-holes of 210-;
The axis of 300- engine shafts;
400- guide vanes;
500- support blades;
510- vane holes.
Specific implementation mode
In order to make the purpose , technical scheme and advantage of the present invention be clearer, by the following examples, it and combines attached
Casing among the turbogenerator of the present invention is further elaborated in figure.It should be appreciated that specific reality described herein
Example is applied only to explain the present invention, is not intended to limit the present invention.
It should be noted that when element is referred to as " being fixed on " another element, it can be directly on another element
Or there may also be elements placed in the middle.When an element is considered as " connection " another element, it can be directly connected to
To another element or it may be simultaneously present centering elements.On the contrary, when element is referred to as " directly existing " another element "upper",
There is no intermediary elements.Term as used herein " vertically ", " horizontal ", "left", "right" and similar statement are
For illustrative purposes.
Casing among the turbogenerator of the present invention, nozzle ring is can be used as while use as support case to be made
With reasonably guiding air-flow by guide vane, and hollow support blade can be used as lubricating oil asphalt channel to ensure axis
Lubrication is held, turboshaft engine etc. is applicable to, usually, intermediate casing upstream connection gas-turbine blade outlet, downstream connection
Free turbine vane inlet.
Casing among the turbogenerator provided referring to Fig. 1 to Fig. 3, one embodiment of the invention, including 100 He of casing outer shroud
Casing inner ring 200, casing outer shroud 100 are set in outside casing inner ring 200, the longitudinal center line of casing outer shroud 100, casing inner ring
200 longitudinal center line is overlapped with the axis of engine shaft 300, between having between casing outer shroud 100 and casing inner ring 200
Every;It is provided with multiple guide vanes 400 between casing outer shroud 100 and casing inner ring 200, multiple guide vanes 400 are around starting
The axis 300 of arbor is circumferential to be uniformly distributed, the direction for guiding air-flow.
The guide vane 400 of airflow direction can be guided by setting so that intermediate casing has the function of air-flow guiding,
To which engine is without in addition setting nozzle ring, engine component is reduced, the arrangement of engine structure, shortening is convenient for start
Machine entire length.
Referring to Fig. 1 and Fig. 4, as a kind of embodiment, one end of each guide vane 400 is all connected with casing outer shroud
100, the other end is all connected with casing inner ring 200, and the leading edge of guide vane 400 and trailing edge are formed by plane and engine shaft
The outflow direction of 300 angled setting of axis, the approach axis and air-flow that make air-flow forms angle, in this way, wind blade can
Air-flow is guided, and the direction of air-flow can be changed as needed.
Further, 300 direction of axis of the approach axis of the air-flow of the edge of guide vane 400 and engine shaft
Angular range is 20 °~70 °;300 direction of axis in the outflow direction and engine shaft of the air-flow at the trailing edge of guide vane 400
Angular range be 50 °~90 °.In this way, under the action of guide vane 400, air-flow is entered with smaller angle, with larger
The intermediate casing of angle outflow, that is to say, that air-flow is flowed out relative to axis 300 with the angle of bigger, by correct guidance air-flow,
Reduce aerodynamic loss.
Wherein, guide vane 400 is three dimendional blade, and blade profile is different at different height section.In 400 leaf of guide vane
In the design of type, 400 edge gas of guide vane can be determined according to known upstream gas-turbine blade outlet flow angle first
Entry angle is flowed, air-flow efflux angle at 400 trailing edge of guide vane is determined according to known downstream free turbine vane inlet flow angle
Degree, Meridian Passage shape is determined according to inner and outer ring flow channel shape.It can be made by curves such as Beziers after into and out of angle-determining
Type method construct mean camber line, and determine the thickness distribution along mean camber line.Rationally product folds rule for selection, as guide vane 400 is optional
It is folded to select leading edge product.A three-dimensional blade profile is can be obtained as a result, above procedure can be in NUMECA/AUTOBLADE by above procedure
It is easily carried out in (cfdrc) software.Can be that blade is excellent by CFD (computational fluid dynamics) result of calculation
Change and guidance is provided, different blade profiles is obtained by adjusting different height cross section curve control point, until obtaining best blade profile knot
Fruit.
Referring to Fig. 1 and Fig. 2, as a kind of embodiment, casing outer shroud 100 passes through multiple supports with casing inner ring 200
Blade 500 connects;Multiple support blades 500 are circumferentially uniformly distributed around the axis 300 of engine shaft, each support blade 500
One end connection casing outer shroud 100, the other end connects casing inner ring 200.
Wherein, support blade 500 as connection casing outer shroud 100 and casing inner ring 200 structure, can be 2,3
It is a, 4 etc., several support blades 500 around engine shaft axis 300 it is circumferential be uniformly distributed after, guide vane 400 also around
The axis 300 of engine shaft is circumferential to be evenly distributed between two adjacent support blades 500.
Referring to Fig. 5, preferably, the blade profile of support blade 500 is consistent with the blade profile of guide vane 400, in this way, support blade
500 while playing the role of support connection casing outer shroud 100 and casing inner ring 200, additionally it is possible to play same guide vane 400
Equally, the effect of air-flow is guided.Herein it should be noted that the installation direction of the support blade 500 also peace with guide vane 400
Dress direction is consistent, in this way, support blade 500 coordinates the change of airflow direction with guide vane 400 change of airflow direction
Unanimously, air turbulence is avoided the occurrence of.Certainly, in other embodiments, the blade profile of support blade 500 can also be with guide vane
400 is inconsistent, such as guide vane 400 is three dimendional blade, and support blade 500 can be prismatic blade, i.e., support blade 500 passes through
The both sides blade for crossing the section of blade inlet edge and trailing edge is symmetrical.
Further, the vane hole 510 through both ends is both provided in each support blade 500, for for lubricating oil pipe
It passes through;It is logical that the first through hole 110 and second being connected to vane hole 510 is respectively arranged on casing outer shroud 100, casing inner ring 200
Hole 210.In such manner, it is possible to solve in turboshaft engine asking for bearing lubricating oil circuit difficult arrangement between gas turbine and free turbine
Topic, by the way that vane hole 510 is arranged in support blade 500, the oil pipe of lubricant passage way can be passed through from vane hole 510 so that lubrication
Oil circuit characteristics of compact layout is not take up space, and effectively lubricating oil can be avoided to be heated by high-temperature fuel gas.
As a kind of embodiment, the cross sectional shape of vane hole 510 is adapted with the cross sectional shape of support blade 500.
In this way, the processing of blade 500 easy to support.
Further, each support blade 500 is the hollow housing of both ends open, and hollow space forms vane hole
510;The shape of first through hole 110, the shape of the second through-hole 210 are consistent with the cross sectional shape of vane hole 510, consequently facilitating profit
Oil pipe passes through.Preferably, the wall thickness of support blade 500 is 2mm or so, the i.e. hole wall of vane hole 510 to support blade
The distance range of 500 outer wall can be 2mm-5mm.And the sectional dimension of vane hole 510 can also design as needed, generally may be used
Primary demand can be met by being extended there through for the lubricating oil pipe that maximum gauge is 8mm-20mm.
Casing among the turbogenerator of the embodiment of the present invention, by be arranged guide vane make air-flow with rational angle into
Enter free turbine blade, while aerodynamic loss can be reduced, by the way that hollow support blade is arranged, makes the reasonable cloth of lubricant passage way
It sets, while lubricating oil being avoided to be heated by high-temperature fuel gas.Structure using the turbogenerator of the intermediate casing is compacter, starts
Machine part quantity, engine weight are reduced, and engine entire length shortens.
Each technical characteristic of embodiment described above can be combined arbitrarily, to keep description succinct, not to above-mentioned reality
It applies all possible combination of each technical characteristic in example to be all described, as long as however, the combination of these technical characteristics is not deposited
In contradiction, it is all considered to be the range of this specification record.
Several embodiments of the invention above described embodiment only expresses, the description thereof is more specific and detailed, but simultaneously
It cannot therefore be construed as limiting the scope of the patent.It should be pointed out that coming for those of ordinary skill in the art
It says, without departing from the inventive concept of the premise, various modifications and improvements can be made, these belong to the protection of the present invention
Range.Therefore, the protection domain of patent of the present invention should be determined by the appended claims.
Claims (9)
1. casing among a kind of turbogenerator, which is characterized in that including casing outer shroud and casing inner ring, the casing exterior ring cap
Be located at outside the casing inner ring, the longitudinal center line of the casing outer shroud, the casing inner ring longitudinal center line with start
The axis of arbor overlaps, and has interval between the casing outer shroud and the casing inner ring;
It is provided with multiple guide vanes between the casing outer shroud and the casing inner ring, multiple guide vanes are around starting
The axis of arbor is circumferentially uniformly distributed, the direction for guiding air-flow.
2. casing among turbogenerator according to claim 1, which is characterized in that one end of each guide vane
It is all connected with the casing outer shroud, the other end is all connected with the casing inner ring, and the leading edge of the guide vane and trailing edge are formed
Plane and engine shaft the angled setting of axis, make air-flow approach axis and air-flow outflow direction formed angle.
3. casing among turbogenerator according to claim 2, which is characterized in that the edge of the guide vane
The angular range of the approach axis of air-flow and the axis direction of engine shaft is 20 °~70 °;
The angular range of the outflow direction of air-flow at the trailing edge of the guide vane and the axis direction of engine shaft is 50 °~
90°。
4. casing among turbogenerator according to claim 1, which is characterized in that the casing outer shroud and the casing
Inner ring is connected by multiple support blades;
Multiple support blades are circumferentially uniformly distributed around the axis of engine shaft, one end connection of each support blade
The casing outer shroud, the other end connect the casing inner ring.
5. casing among turbogenerator according to claim 4, which is characterized in that be all provided in each support blade
It is equipped with the vane hole through both ends, for being passed through for lubricating oil pipe;It is respectively arranged on the casing outer shroud, the casing inner ring
The first through hole being connected to the vane hole and the second through-hole.
6. casing among turbogenerator according to claim 5, which is characterized in that the cross sectional shape of the vane hole with
The cross sectional shape of the support blade is adapted.
7. casing among turbogenerator according to claim 5, which is characterized in that each support blade is two
The hollow housing of end opening, hollow space form the vane hole;
The shape of the first through hole, the shape of second through-hole are consistent with the cross sectional shape of the vane hole.
8. casing among turbogenerator according to claim 6, which is characterized in that along the leading edge of the support blade
To the direction of trailing edge, the numberical range of the cross-sectional width of the vane hole is 8mm-20mm.
9. casing among turbogenerator according to claim 4, which is characterized in that the blade profile of the support blade and institute
The blade profile for stating guide vane is consistent.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710228722.6A CN108691583A (en) | 2017-04-10 | 2017-04-10 | Casing among turbogenerator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710228722.6A CN108691583A (en) | 2017-04-10 | 2017-04-10 | Casing among turbogenerator |
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| Publication Number | Publication Date |
|---|---|
| CN108691583A true CN108691583A (en) | 2018-10-23 |
Family
ID=63842340
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710228722.6A Pending CN108691583A (en) | 2017-04-10 | 2017-04-10 | Casing among turbogenerator |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112377269A (en) * | 2021-01-11 | 2021-02-19 | 中国空气动力研究与发展中心高速空气动力研究所 | Anti-distortion stator design method suitable for contra-rotating lift propulsion device |
| CN112960139A (en) * | 2021-02-26 | 2021-06-15 | 中国人民解放军空军工程大学 | To vortex flow distortion generator |
| CN113738530A (en) * | 2021-10-15 | 2021-12-03 | 清华大学 | Multi-duct aero-engine casing structure with blade tip fan |
| CN113864239A (en) * | 2021-10-27 | 2021-12-31 | 中国航发沈阳发动机研究所 | Double-duct aero-engine high-low pressure gas engine and intermediate casing part thereof |
| CN113959834A (en) * | 2021-10-13 | 2022-01-21 | 中国航发湖南动力机械研究所 | CMC outer ring test piece clamp with low additional thermal stress |
| CN114295382A (en) * | 2021-12-22 | 2022-04-08 | 北京动力机械研究所 | Air inlet casing of high-pressure turbine blade vibration stress dynamic measurement core machine tester |
| CN114542207A (en) * | 2022-02-22 | 2022-05-27 | 中国航发沈阳发动机研究所 | Design method for outer surface modeling of turbine rear casing support plate |
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|---|---|---|---|---|
| GB756976A (en) * | 1954-02-18 | 1956-09-12 | Rolls Royce | Improvements in or relating to lubricating systems for gas-turbine engines |
| US20110081239A1 (en) * | 2009-10-01 | 2011-04-07 | Pratt & Whitney Canada Corp. | Fabricated static vane ring |
| CN204419278U (en) * | 2014-12-23 | 2015-06-24 | 宁国市华成金研科技有限公司 | Nozzle ring |
| EP3064716A1 (en) * | 2015-03-06 | 2016-09-07 | United Technologies Corporation | Mid turbine frame with integrated inner case heat shield |
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2017
- 2017-04-10 CN CN201710228722.6A patent/CN108691583A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB756976A (en) * | 1954-02-18 | 1956-09-12 | Rolls Royce | Improvements in or relating to lubricating systems for gas-turbine engines |
| US20110081239A1 (en) * | 2009-10-01 | 2011-04-07 | Pratt & Whitney Canada Corp. | Fabricated static vane ring |
| CN204419278U (en) * | 2014-12-23 | 2015-06-24 | 宁国市华成金研科技有限公司 | Nozzle ring |
| EP3064716A1 (en) * | 2015-03-06 | 2016-09-07 | United Technologies Corporation | Mid turbine frame with integrated inner case heat shield |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112377269A (en) * | 2021-01-11 | 2021-02-19 | 中国空气动力研究与发展中心高速空气动力研究所 | Anti-distortion stator design method suitable for contra-rotating lift propulsion device |
| CN112960139A (en) * | 2021-02-26 | 2021-06-15 | 中国人民解放军空军工程大学 | To vortex flow distortion generator |
| CN112960139B (en) * | 2021-02-26 | 2022-09-20 | 中国人民解放军空军工程大学 | To vortex flow distortion generator |
| CN113959834A (en) * | 2021-10-13 | 2022-01-21 | 中国航发湖南动力机械研究所 | CMC outer ring test piece clamp with low additional thermal stress |
| CN113738530A (en) * | 2021-10-15 | 2021-12-03 | 清华大学 | Multi-duct aero-engine casing structure with blade tip fan |
| CN113864239A (en) * | 2021-10-27 | 2021-12-31 | 中国航发沈阳发动机研究所 | Double-duct aero-engine high-low pressure gas engine and intermediate casing part thereof |
| CN114295382A (en) * | 2021-12-22 | 2022-04-08 | 北京动力机械研究所 | Air inlet casing of high-pressure turbine blade vibration stress dynamic measurement core machine tester |
| CN114542207A (en) * | 2022-02-22 | 2022-05-27 | 中国航发沈阳发动机研究所 | Design method for outer surface modeling of turbine rear casing support plate |
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Application publication date: 20181023 |
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