CN109563743A - Pillar for aircraft engine - Google Patents
Pillar for aircraft engine Download PDFInfo
- Publication number
- CN109563743A CN109563743A CN201780050316.3A CN201780050316A CN109563743A CN 109563743 A CN109563743 A CN 109563743A CN 201780050316 A CN201780050316 A CN 201780050316A CN 109563743 A CN109563743 A CN 109563743A
- Authority
- CN
- China
- Prior art keywords
- pillar
- thickness
- main body
- centre portion
- interior zone
- 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.)
- Pending
Links
Classifications
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- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/542—Bladed diffusers
-
- 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
- F01D9/047—Nozzle boxes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
- F05D2240/128—Nozzles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/14—Casings or housings protecting or supporting assemblies within
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
A kind of pillar for gas-turbine unit, the main body including limiting first side and opposite second side.First side is spaced apart along the circumferential direction of gas-turbine unit with second side.Additionally, main body includes interior zone, centre portion and outer sections.Each of interior zone, centre portion and outer sections are arranged along the span of pillar by series sequence, and the thickness between the first side and second side of restriction pillar.The thickness of centre portion is greater than the thickness of interior zone and the thickness of outer sections, to increase the drag for buckling of pillar in response to the power being applied on pillar.
Description
The research that federal government initiates
The present invention is to be made at the contract number FA8650-09-D-2922 of United States Air Force using governmental support.Government can be with
Possess certain rights in the present invention.
Technical field
This theme relates generally to the pillar for aircraft engine.
Background technique
Gas-turbine unit includes fan section and core-engine.Core-engine includes: by axial series flow relationship
High pressure compressor, to compress the air stream for entering core-engine；Burner, wherein the mixture of fuel and the air of compression is burnt
It burns, to generate propulsion air-flow；And high-pressure turbine, by promoting air-flow to rotate, and it is connected by axis to drive
High pressure compressor.Low-pressure turbine is made an addition to the rear portion of high-pressure turbine by typical by-pass turbofan engine, and low-pressure turbine drives position
In the fan of the fan section of the front of high pressure compressor.The fan flow that the current divider at fan rear portion will move out fan is divided into core
Engine stream and bypass stream around core-engine.
Fan section includes one or more levels fan rotor blade and strut assemblies.Strut assemblies are included at radial inner end
It is installed to hub and is installed to the circumferentially spaced pillar of package shell body at radial outer end.Outer housing limits circular shape,
So that limiting round flow path surfaces for the flow path for passing through fan section.
The pillar of strut assemblies allows for the relatively large power for bearing to generate during the operation of gas-turbine unit.
These power may include the static force of the weight of the various components from gas-turbine unit and for example including combustion gas whirlpool
The dynamic force generated during certain maneuvers of the aircraft of turbine.During the operation of gas-turbine unit, this
A little power can promote pillar buckling.Pillar is typically formed in thick and relatively robust mode, to bear static force and dynamic
Power.However, may cause the relatively heavy pillar of strut assemblies in this way.
Therefore, it will be useful for capable of more preferably bearing the pillar of static force and dynamic force.In addition, in the totality for mitigating pillar
While weight, it will be particularly beneficial for capable of more preferably bearing the pillar of static force and dynamic force.
Summary of the invention
Aspects and advantages of the present invention will be partly articulated in the following description, or can from description it is clear that or
It can be learnt by practicing the present invention.
In an exemplary embodiment of the disclosure, provides a kind of gas turbine for limiting circumferential direction and start
The pillar of machine.Pillar limits the span, and the main body including limiting first side and opposite second side.First side is along week
It is spaced apart to direction with second side.Main body includes the interior zone arranged along the span of pillar by series sequence, middle area
Section and outer sections.Interior zone, centre portion and outer sections respectively limit between first side and second side
Thickness.The thickness of centre portion is greater than the thickness of interior zone and outer sections.
In another exemplary embodiment of the present disclosure, a kind of gas turbine for limiting circumferential direction is provided to start
The strut assemblies of machine.Strut assemblies include interior hub and external structure shell.Strut assemblies are additionally included in interior hub and external structure shell
The pillar extended between body.Pillar limits the span and extends through the middle line of the thick of pillar along the span.Pillar also limits
Determine first side and opposite second side, first side is spaced apart with second side along the circumferential direction.Pillar include along
Interior zone, centre portion and the outer sections of series sequence arrangement are pressed in the span of pillar.Interior zone, centre portion and
Outer sections respectively limit the thickness extended through between the first side of middle line and second side.The thickness of centre portion is greater than
The thickness of interior zone and centre portion.
With reference to following description and appended claims, these and other feature of the invention, side will be more clearly understood
Face and advantage.It is incorporated in this manual and forms drawing illustration the embodiment of the present invention of a part of this specification, and
And attached drawing is together with description principle used to explain the present invention.
Detailed description of the invention
Illustrate in the description for those of ordinary skill in the art of the invention detailed and open disclosure (including this
The optimal mode of invention), this is carried out with reference to attached drawing illustrates, in the accompanying drawings:
Fig. 1 is the schematic cross section according to the exemplary gas turbogenerator of the various embodiments of this theme.
Fig. 2 is the spy of the front standing pillar component (also referred to as forward frame component) of the exemplary gas turbogenerator of Fig. 1
Write schematic cross section.
Fig. 3 is the isolated axial view of the exemplary front standing pillar component of Fig. 2.
Fig. 4 is the external structure shell according to the exemplary front standing pillar component for being attached to Fig. 2 of the illustrative aspect of the disclosure
Pillar close up view.
Fig. 5 is the side view according to the pillar of the exemplary front standing pillar component of Fig. 2 of the illustrative aspect of the disclosure.
Fig. 6 is the spanwise cross-sectional view along the exemplary strut of the line 6-6 of Fig. 5 Fig. 5 intercepted.
Fig. 7 is the spanwise cross-sectional view along the exemplary strut of the line 7-7 of Fig. 5 Fig. 5 intercepted.
Fig. 8 is the spanwise cross-sectional view along the exemplary strut of the line 8-8 of Fig. 5 Fig. 5 intercepted.
Fig. 9 is the figure with graph making along the thickness of the exemplary strut of Fig. 5 of the middle line of the exemplary strut of Fig. 5
Solution.
Specific embodiment
Reference will now be made in detail to the present embodiment of the invention, illustrate one or more examples of the invention in the accompanying drawings.
Detailed description refers to the feature in attached drawing using number mark and letter designation.Same or similar mark in attached drawing and description
It has been used for referring to same or similar part of the invention.As used herein, term " first ", " second " and " third "
It can be used interchangeably, a component is distinguished with another, and be not intended to the position for showing an other component or again
The property wanted.Term " upstream " and " downstream " refer to the relative direction relative to the fluid stream in fluid passage.For example, " upstream " refers to fluid
The direction of stream certainly, also, " downstream " refers to the direction that fluid is flow to.
Fig. 1 is schematically illustrated according to the aircraft gas turbine engines 10 of one embodiment of the disclosure.Combustion gas whirlpool
Turbine 10 limits axial direction A, radial direction R and circumferential direction C and (that is, referring to Fig. 3, extends around axial direction A
Direction).Gas-turbine unit 10 include axially A extend engine centerline 12 (it is described with hachure, for
With reference to), and there is fan section 14, high pressure compressor 16, burning block 18, high-pressure turbine 20 and low pressure whirlpool with series flow relationship
Wheel 22.High pressure compressor 16, burning block 18 and high-pressure turbine 20 are commonly known as core-engine 24.
Fan section 14 is illustrated as with the first order fan blade 26A being respectively arranged in ring-type fan conduit 28, the
The multistage fan section of second level fan blade 26B and third level fan blade 26C.Fan section 14 is additionally including at least portion
Divide the strut assemblies of ground support fan section 14.Specifically, for discribed embodiment, fan section 14 includes being located at first
The front standing pillar component 30 of the front of grade fan blade 26A.Additionally, fan section 14 includes adjacent to first order fan blade
The grade of 26A, second level fan blade 26B and the guiding guide vane of each configuration in third level fan blade 26C.Specifically,
Discribed exemplary fan section 14 includes the first order guiding guide vane 32A, position positioned at the rear portion of first order fan blade 26A
Guide vane 32B is oriented in the second level at the rear portion of second level fan blade 26B and positioned at the rear portion of third level fan blade 26C
The third level is oriented to guide vane 32C.It is each that the first order is oriented to guide vane 32A, second level guiding guide vane 32B and third level guiding guide vane 32C
It is configured from C along the circumferential direction around engine centerline 12.In certain embodiments, third level guiding guide vane 32C can be into
One step is configured to pillar.
Fan air 34 exits fan section 14, also, annular splitter 36 is split into fan air 34 across bypass
Conduit 40 is transmitted to core-engine around the bypath air part 38 around core-engine 24, and across diffusion conduit 44
Core engine air part 42 in 24.Fan frame 46 is located at the rear end of fan section 14, and fan frame 46 includes week
The multiple structural posts 48 configured to ground.Pillar 48 across by-pass conduit 40 fan by-pass entrance 50 and diffusion conduit 44 core
Heart motor inlet 52 and radially.Current divider 36 is segmented and is attached to pillar 48, also, current divider 36 is in fan by-pass
Axially extend between entrance 50 and core engine inlet 52.
In core-engine 24, high pressure rotor axis 54 makes high-pressure turbine 20 be connected to high pressure compressor with driving relationship
16, also, low pressure rotor axis 56 makes low-pressure turbine 22 be drivingly connected to fan section 14.Fuel is burnt in burning block 18
It burns, generates thermal current 58 (it is directed respectively across high-pressure turbine 20 and low-pressure turbine 22), to provide power to engine 10.
Thermal current 58 is discharged into the exhaust section 60 of engine 10, and at this, thermal current 58 is empty with the bypass from by-pass conduit 40
Gas part 38 mixes, and passes through the variable-nozzle 62 at the rear end of engine 10 and be discharged.After burner 64 can be used for thrust
Enhancing.Illustrated example engine 10 is that the typical case of military gas turbine aircraft engines 10 is (such as, general in Fig. 1
The F-110 of electric corporation).
It is to be appreciated, however, that exemplary gas turbogenerator 10 depicted in figure 1 is only provided via example,
And in the other embodiments of the disclosure, gas-turbine unit 10 can have any other suitable form or construction.Example
Such as, in other exemplary embodiments of the invention, gas-turbine unit 10 can additionally include low pressure compressor, be located at HP and compress
The front of machine 16 and the rear portion of fan section 14.Moreover, gas-turbine unit can change there are also in some other embodiment
To be configured to any other suitable fanjet, turboshaft engine, turbo oar engine etc..
Referring now to Fig. 2 and Fig. 3, provide fan section 14 (or more specifically, the exemplary engine 10 of Fig. 1 fan
The front standing pillar component 30 of section 14) figure.Specifically, Fig. 2 provide be assemblied in engine 10 describe in Fig. 1 it is exemplary
The feature side cross-sectional view of the front standing pillar component 30 of fan section 14, also, Fig. 3 provides exemplary wind depicted in figure 1
The isolated axial view of the front standing pillar component 30 of sector field 14.
As most clearly described in Fig. 2, front standing pillar component 30 supports the multistage fan leaf of exemplary fan section 14
The rotation of piece 26A, 26B, 26C.More specifically, front standing pillar component 30 include between external structure shell 72 and interior hub 74 generally
The multiple pillars 66 extended along radial direction R.For discribed embodiment, each pillar 66 generally includes inner end 78
The main body 76 that extends between outer end 80, the interior mounting flange 82 being integrally formed at the inner end of main body 76 78 with main body 76,
And the outer mounting flange 84 being integrally formed at the outer end of main body 76 80 with main body 76.Interior mounting flange 82 is configured to be used for
It is attached to interior hub 74, also, outer mounting flange 84 is configured for attachment to external structure shell 72.Additionally, front standing pillar component
30 external structure shell 72 is then configured for attachment to the frame or cabin (not describing) of engine 10.Notably,
Discribed exemplary engine 10 further includes the preceding seal member being used to form with the sealing of the frame of engine 10 or cabin
86。
Particularly still referring to Figure 2, the interior hub 74 of front standing pillar component 30 is attached to bearing case 88.For discribed reality
Example is applied, interior hub 74 is bolted to bearing case 88 by multiple bolts 90.The encapsulating of bearing case 88 is used to support fan area
The forefan bearing 92 of the rotor assembly 94 of section 14.As discussed hereinabove, the rotor assembly 94 of fan section 14 can be attached
It is connected to the LP axis 56 of engine 10, or can be the extension of the LP axis 56 of engine 10.In certain embodiments, forward fan shaft
92 are held it is so structured that ball bearing, roller bearing or any other suitable bearing.
In addition, each of multiple pillars 66 of front standing pillar component 30 are configured with guiding guide vane 96.It is oriented in guide vane 96
It is each positioned at the just rearward of corresponding pillar 66, and can be operated together with variable guiding guide vane system 98.Variable guiding guide vane
System 98 is configured to rotate each of multiple guiding guide vanes 96 around guiding guide vane axis 100, so that multiple guiding guide vanes
96 can guide the air stream entered in fan section 14 on front standing pillar component 30 in the desired manner.
Referring now specifically to Fig. 3, and as will be discussed in more detail below, discribed exemplary front standing pillar group
Part 30 includes the multiple pillars 66 formed in such manner, to have the drag of the increase for buckling.Therefore, exemplary front standing pillar
Component 30 may require less pillar 66 to support the expected power measured.For example, exemplary front standing pillar component 30 include along
13 (13) circumferential direction C spaced apart it is a it is a with 21 (21) between number pillar 66.Specifically for being described
Embodiment, front standing pillar component 30 include a pillar 66 in 13 (13).However, in other embodiments, front standing pillar component 30 can
Be changed to include any other suitable quantity pillar 66.In certain embodiments, multiple pillars 66 can be circumferentially square
Essentially homogeneously be spaced apart to C, or in other embodiments, multiple pillars 66 can with C along the circumferential direction asymmetrically between
It separates.
Moreover, interior hub 74 limits interior hub radius 102, also, external structure shell 72 similarly limits external structure shell radius
104.Interior hub radius 102 and external structure shell radius 104 are respectively defined as from longitudinal center line 12 along radial direction R to phase
The mounting surface answered.More specifically, interior hub radius 102 is defined as from longitudinal center line 12 along radial direction R to interior hub 74
Mounting surface 106.Notably, the mounting surface 106 of interior hub 74 is limited relative to axial direction for discribed embodiment
The angle (referring to fig. 2) of center line 12.Therefore, hub radius 102 is more specifically limited to from axial direction discribed embodiment
Center line 12 along the mounting surface 106 of radial direction R to interior hub 74 rear end.Similarly, external structure shell radius 104 is limited
It is set to the mounting surface 108 for being limited to external structure shell 72 along radial direction R from longitudinal center line 12.
In view of the pillar 66 of exemplary front standing pillar component 30 is able to bear the power of the amount of increase, it may be required that less branch
Column, it means that the size of interior hub 74 can reduce (because, it is desirable that lesser surface area in mounting surface 106 is installed
Pillar 66).Therefore, the ratio of interior hub radius 102 and external structure shell radius 104 also can reduce.For example, for discribed reality
Apply example, the ratio of interior hub radius 102 and external structure shell radius 104 is less than about 1:4.It should be recognized that approximate term is (such as,
" about " or " approximatively ") refer in the error margin for belonging to 10%.
For discribed embodiment, the interior hub 74 of front standing pillar component 30 limits substantially circular shape, and therefore, peace
It is substantially circular for filling surface 106 similarly.External structure shell 72 includes multiple installation pads 110 and multiple shell attachments
112.Each of multiple shell attachments 112 extend between adjacent installation pad 110, connect adjacent installation pad 110.
For discribed embodiment, multiple installation each of pads 110 and shell attachment 112 prolong along substantially straight direction
It stretches, so that external structure shell 72 generally limits the shape of polygon.Therefore, mounting surface 108 is similarly substantially straight
's.It is to be appreciated, however, that in other exemplary embodiments of the invention, external structure shell 72 is readily modified as being configured to limit substantially
Circular shape.
As used herein, before referring to restriction ratio with reference to the term " substantially straight " of multiple shell attachments 112
The specific shell of the radius of curvature of the big at least twice of the radical length of one or more of multiple pillars 66 of strut assemblies 30
Body attachment 112.It is fully encapsulated in shell attachment 112 moreover, term " substantially straight " can also refer to be limited to
Adjacent installation pad 110 (shell attachment 112 extends therebetween) between the shell of straight reference line that extends along straight direction
Body attachment 112.
As hereinbefore briefly discussed, each of multiple pillars 66 include that corresponding pillar 66 is attached to interior hub
74 interior mounting flange 82 and the outer mounting flange 84 that corresponding pillar 66 is attached to external structure shell 72.More specifically, every
Pillar 66 is attached to the corresponding installation pad 110 of external structure shell 72 by the outer mounting flange 84 of a corresponding pillar 66.
Fig. 4 is equally briefly referred to now, in multiple pillars 66 that the installation pad 110 for being attached to external structure shell 72 is provided
A pillar 66 outer mounting flange 84 close up view.For discribed embodiment, the outer mounting flange 84 of multiple pillars 66
It is configured to T-flange.As noted, outer mounting flange 84 (it is configured to T-flange for discribed embodiment)
It is integrally formed at the outer end of pillar 66 80 with the main body 76 of pillar 66.T shape mounting flange includes for installing pillar 66
The protruding portion 114 relatively extended.Specifically, strut assemblies 30 include being positioned to 110 phase of installation pad corresponding with T-flange
Pair mounting bracket/plate 116 and the mounting plate 118 that is positioned on the inner surface of the protruding portion 114 relatively extended.For being retouched
The embodiment drawn, bolt 120 extend from mounting bracket 116, install pad 110, across the protrusion relatively extended across corresponding
Portion 114 and arrive mounting plate 118.It should be recognized that outwardly extending protruding portion 114 respectively limits for discribed embodiment
Thickness TP.Thickness TPIt is limited substantially along radial direction R.Additionally, for exemplary strut component described herein
30, each of multiple pillars 66 include that (it is configured to for pillar 66 to be attached to corresponding installation pad 110 outer mounting flange 84
T-flange) and similar fashion.
Referring again to FIGS. 3, multiple installation pads 110 and shell attachment 112 are by composite material for discribed embodiment
It is integrally formed.For example, in certain embodiments, each of multiple installation pads 110 and shell attachment 112 can be by carbon fibers
The composite material or any other suitable composite material for tieing up enhancing are formed.
Additionally, each of multiple shell attachments 112 limit inner surface 122 (that is, diameter is inside along radial direction R
Surface), by as being discussed below, also axially and extend circumferentially over upon.It is multiple in view of for discribed embodiment
Each of shell attachment 112 extends between adjacent installation pad 110 along substantially straight direction, when axially square
When observing to A, the inner radial surface 106 of shell attachment 112 limits non-circular shape (that is, polygonal shape) together.In order to
Allow external structure shell 72 limit for aerodynamic purpose and closer similar with circle flow path surfaces 124 (that is, conduct
The inner radial surface of whole external structure shell 72 limits the flow path across fan section 14), front standing pillar component 30 further includes
The multiple wedge-shaped members 126 positioned along the inner surface 106 of shell attachment 112 adjacent to installation pad 110.For certain examples
Property embodiment, it is (such as, adjacent in wedge-shaped member 126 that each of multiple wedge-shaped members 126 can extend up to various length
It is bordering on 30 the percent and hundred of the length (that is, adjacent the distance between installation pad 110) of the shell attachment 112 of its positioning
Between/five ten).Notably, the length of wedge-shaped member 126 can change with the variation of the spacing of pillar 66, branch
Column 66, which can be spaced, to be reached between 24 ° or 30 °, and can have two or more different pitch angles between pillar 66.
Referring now to Figure 5, providing the single of the exemplary front standing pillar component 30 described above by referring to Fig. 2 to Fig. 4
The isolated side view of pillar 66.As shown, pillar 66 limits the span S extended along the length of pillar 66.Additionally, as first
It is preceding discussed, pillar 66 include the main body 76 for limiting inner end 78 and outer end 80, at the outer end of main body 76 80 with main body 76 1
The outer mounting flange 84 formed to body and the interior mounting flange being integrally formed at the inner end of main body 76 78 with main body 76
82.As similarly discribed, the main body 76 of pillar 66 limits front end 128 and rear end 130.Discribed exemplary strut 66 can
(referring to fig. 2) is operated together with guiding guide vane 96 at rear end 130.
In addition, the main body 76 of pillar 66 include the interior zone 132 arranged along the span S of pillar 66 by series sequence,
Centre portion 134 and outer sections 136.For discribed embodiment, interior zone 132 includes the span S's of pillar 66
30 (30%) percent inside approximatively, centre portion 134 includes the approximatively centre 40 percent of the span S of pillar 66
(40%), also, the span S of outer sections 136 including pillar 66 approximatively external 30 (30%) percent.
It reference will also be made to Fig. 6 to Fig. 8 now.Fig. 6 provides the span side of the main body 76 of the pillar 66 along the line 6-6 in Fig. 5
To cross-sectional view；Fig. 7 provides the spanwise cross-sectional view of the main body 76 of the pillar 66 along the line 7-7 in Fig. 5；Also, Fig. 8
The spanwise cross-sectional view of the main body 76 of pillar 66 along the line 8-8 in Fig. 5 is provided.More specifically, Fig. 6 provides pillar 66
Main body 76 outer sections 136 spanwise cross-sectional view, Fig. 7 provides the centre portion 134 of the main body 76 of pillar 66
Spanwise cross-sectional view, also, Fig. 8 provides the spanwise cross-sectional view of the interior zone 132 of the main body 76 of pillar 66.
If Fig. 6 is to depicted in figure 8, the main body 76 of pillar 66 further limits first side 138 and opposite second
Side 140, first side 138 are spaced along the circumferential direction C (referring to Fig. 3) and second side 140 of gas-turbine unit 10
It opens.Additionally, outer sections 136 limit the outside thickness T between first side 138 and second side 140O, centre portion 134
Limit the interior thickness T between first side 138 and second side 140M, also, interior zone 132 limits first side 138
Inner thickness T between second side 140I.The interior thickness T of centre portion 134MGreater than the outside thickness of outer sections 136
TOWith the inner thickness T of interior zone 132I, to improve the bearing capacity of pillar 66.Therefore, Fig. 5 is to pillar depicted in figure 8
66 include bigger intermediate span thickness.
Moreover, for discribed embodiment, inner thickness TI, interior thickness TMAnd outside thickness TOIt is close to pillar
The rear end 130 (that is, than front end 128 closer to rear end 130) of 66 main body 76 and measure.More specifically, main body 76 limit from
Inner end 78 is to outer end 80 and along the middle line 142 of span S extension.Middle line 142 extends through the thickest portion of the main body 76 of pillar 66
Point.For discribed embodiment, the inner thickness T of interior zone 132I, centre portion 134 interior thickness TMAnd it is external
The outside thickness T of section 136OIt is each passed through middle line 142 and measures.
In certain embodiments, the interior thickness T of centre portion 134MIt can be than the inner thickness T of interior zone 132IWith
The outside thickness T of outer sections 136OBig at least about 10%.For example, in certain embodiments, the thick middle of centre portion 134
Spend TMIt can be than the inner thickness T of interior zone 132IWith the outside thickness T of outer sections 136OBig at least about 15%.However,
In other embodiments, interior thickness TMIt is readily modified as than inner thickness TIWith outside thickness TOGreatly less than 10%.
Fig. 9 is equally briefly referred to now, is provided to illustrate and draw across middle line 142 and along the span S's of pillar 66
The chart of the thickness of the main body 76 of pillar 66.As depicted, the inner thickness T of interior zone 132IBe across middle line 142 and
The minimum thickness of the interior zone 132 of measurement, the outside thickness T of outer sections 136OIt is similarly to be measured across middle line 142
Outer sections 136 minimum thickness, also, the thickness of centre portion 134 be across middle line 142 and measure centre portion
134 maximum gauge.As similarly as shown in the chart in Fig. 9, for discribed embodiment, the main body 76 of pillar 66
Across middle line 142 thickness at inner end 78 from inner thickness TIIncrease, and from outside thickness T at outer end 80OIncrease.In this way
Thickness increase can be used for providing bigger strength and stability at interior mounting flange 82 and outer mounting flange 84 respectively.
Referring again to the spanwise cross-sectional view of Fig. 6 to Fig. 8, for discribed embodiment, the main body 76 of pillar 66
Hollow cavity 144 is limited between first side 138 and second side 140 for discribed embodiment.Hollow cavity 144 is in master
The outer end 80 of main body 76 is substantially extended in body 76 from the inner end of main body 76 78.Before hollow cavity 144 is positioned at middle line 142
Portion allows hollow cavity 144 to mitigate the weight of pillar 66, and does not reduce the intensity of pillar 66 not significantly, or more particularly, and
Pillar 66 is not reduced not significantly for the drag of buckling power.It is to be appreciated, however, that in other embodiments, pillar 66 may
Chamber 144 is not limited.
Notably, pillar 66 can be formed by composite material as external structure shell 72.For example, pillar 66
It can be formed by carbon fibre reinforcement.However, alternatively, in other embodiments, pillar 66 can be by any other suitable
Composite material formed.Since pillar 66 can be formed by composite material, thus the plate layer of formation pillar 66 or layer can be in masters
It is separated at the inner end 78 and outer end 80 of body 76, to form interior mounting flange 82 and outer mounting flange 84.Therefore, as hereinbefore joined
It examines Fig. 4 and notices, the protruding portion 114 of outer mounting flange 84 (that is, being configured to T shape mounting flange) relatively extended limits
Thickness TP.The thickness T of the protruding portion 114 relatively extendedPIt is less than or equal to the outside of main body 76 for discribed embodiment
The outside thickness T of section 136OIt is approximately half of.However, in other exemplary embodiments of the invention, outer mounting flange 84 can be to appoint
What its suitable mode forms to include having any other suitable thickness TOProtruding portion 114.
Including have the strut assemblies of pillar formed according to one or more the present embodiment can permit much more resistant to
The stronger pillar of buckling power.Specifically, as it will be realized, including that bigger intermediate span thickness increases pillar for bending
Bent drag.Meanwhile formed according to one or more of the present embodiment of composite material pillar can also mitigate pillar and
The weight of corresponding strut assemblies.
This written description uses examples to disclose the present invention, including optimal mode, and also makes any person skilled in the art
The present invention can be practiced, including production and using any device or system and executes any method being incorporated to.Patent of the invention
Range is defined by the claims, and may include the other examples that those skilled in the art are expected.Other show if such
Example includes the not structural detail different from the literal language of claim, or if these examples include having and claim
Literal language unsubstantiality difference equivalent structural detail, then these examples are intended to belong in the scope of the claims.
Claims (20)
1. a kind of for limiting the pillar of the gas-turbine unit of circumferential direction, the pillar limits the span and includes:
The main body of first side and opposite second side is limited, the first side is along the circumferential direction and described second
Side is spaced apart, and the main body includes the interior zone arranged along the span of the pillar by series sequence, middle area
Section and outer sections, the interior zone, centre portion and outer sections respectively limit the first side and described the
Thickness between two side faces, the thickness of the centre portion are greater than the thickness of the interior zone and the outer sections.
2. pillar according to claim 1, which is characterized in that the pillar is formed by composite material.
3. pillar according to claim 1, which is characterized in that the thickness of the centre portion is thicker than the interior zone
Thickness at least about 10 (10%) greatly of degree and the outer sections.
4. pillar according to claim 1, which is characterized in that the thickness of the centre portion is thicker than the interior zone
The thickness greatly at least about 1 15 (15%) of degree and the centre portion.
5. pillar according to claim 1, which is characterized in that the interior zone includes the span of the pillar
Inside 30 percent, wherein the centre portion includes the centre 40 percent of the span of the pillar, and wherein
The outer sections include the outside 30 percent of the span of the pillar.
6. pillar according to claim 1, which is characterized in that the interior zone, centre portion and outer sections
Thickness is respectively to measure close to the rear end of the pillar.
7. pillar according to claim 1, which is characterized in that the main body limits inner end and outer end, wherein the pillar
Limit the middle line that the outer end is extended to from the inner end across the thick of the main body, and wherein the interior zone,
Centre portion and the thickness of outer sections are measured across the middle line.
8. pillar according to claim 7, which is characterized in that the thickness of the interior zone be the interior zone most
Small thickness, wherein the thickness of the outer sections is the minimum thickness of the outer sections, and the wherein thickness of the centre portion
Degree is the maximum gauge of the centre portion.
9. pillar according to claim 1, which is characterized in that the main body restriction substantially extends to institute from the inner end
State the hollow cavity between the first surface and the second surface of outer end.
10. pillar according to claim 1, which is characterized in that the main body limits inner end and outer end, wherein the pillar
It further include the outer T shape mounting flange being integrally formed at the outer end of the main body with the main body.
11. pillar according to claim 10, which is characterized in that the T shape mounting flange includes for installing the branch
The protruding portion of column relatively extended wherein the protruding portion relatively extended limits thickness, and wherein described relatively prolongs
The thickness for the protruding portion stretched is less than or equal to the approximately half of of the thickness of the outer sections.
12. a kind of for limiting the strut assemblies of the gas-turbine unit of circumferential direction, the strut assemblies include:
Interior hub；
External structure shell；And
Pillar extends between the interior hub and the external structure shell, and the pillar limits the span and along the span
The middle line of the thick of the pillar is extended through, the pillar further defines first side and opposite second side, described
First side is spaced apart along the circumferential direction with the second side, and the pillar includes the wing along the pillar
Interior zone, centre portion and outer sections of the exhibition by series sequence arrangement, the interior zone, centre portion and outside
Section respectively limits the thickness extended through between the first side of the middle line and the second side, the middle area
The thickness of section is bigger than the thickness of the interior zone and the centre portion.
13. strut assemblies according to claim 12, which is characterized in that the main body limits inner end and outer end, wherein institute
It states middle line and extends to the outer end from the inner end.
14. strut assemblies according to claim 12, which is characterized in that the thickness of the interior zone is the inner area
The minimum thickness of section, wherein the thickness of the outer sections is the minimum thickness of the outer sections, and the wherein middle area
The thickness of section is the maximum gauge of the centre portion.
15. strut assemblies according to claim 12, which is characterized in that the thickness of the centre portion is than the inner area
The thickness of section and the thickness greatly at least about 10% of the centre portion.
16. strut assemblies according to claim 12, which is characterized in that the main body limits inner end and outer end, wherein institute
Stating main body includes the outer T shape mounting flange at the outer end.
17. strut assemblies according to claim 16, which is characterized in that the T shape mounting flange includes for installing
The protruding portion of pillar relatively extended is stated, wherein the protruding portion relatively extended limits thickness, and wherein described opposite
The thickness for the protruding portion that ground extends is the approximately half of of the thickness of the outer sections.
18. strut assemblies according to claim 12, which is characterized in that the strut assemblies are for the gas turbine
The front standing pillar component of the fan section of engine.
19. strut assemblies according to claim 12, which is characterized in that the pillar includes multiple pillars, wherein described
Multiple pillars include the pillar of the number between 13 and 21.
20. strut assemblies according to claim 12, which is characterized in that the strut assemblies limit interior hub radius and outer knot
Structure shell radius, and wherein the ratio of the interior hub radius and the external structure shell radius is less than about 1:4.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US15/236,745 US20180045221A1 (en) | 2016-08-15 | 2016-08-15 | Strut for an aircraft engine |
| US15/236745 | 2016-08-15 | ||
| PCT/US2017/037791 WO2018034729A1 (en) | 2016-08-15 | 2017-06-15 | Strut for an aircraft engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109563743A true CN109563743A (en) | 2019-04-02 |
Family
ID=59153347
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201780050316.3A Pending CN109563743A (en) | 2016-08-15 | 2017-06-15 | Pillar for aircraft engine |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US20180045221A1 (en) |
| EP (1) | EP3497306A1 (en) |
| CN (1) | CN109563743A (en) |
| CA (1) | CA3033186A1 (en) |
| WO (1) | WO2018034729A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110645052A (en) * | 2019-10-24 | 2020-01-03 | 周宇凡 | Turbine of aircraft engine |
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| US20120051923A1 (en) * | 2010-08-31 | 2012-03-01 | Mcdonald Seth Alexander | Composite vane mounting |
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| US8096746B2 (en) * | 2007-12-13 | 2012-01-17 | Pratt & Whitney Canada Corp. | Radial loading element for turbine vane |
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| WO2014158283A1 (en) * | 2013-03-14 | 2014-10-02 | Bronwyn Power | A subsonic shock strut |
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- 2017-06-15 WO PCT/US2017/037791 patent/WO2018034729A1/en unknown
- 2017-06-15 EP EP17732717.8A patent/EP3497306A1/en not_active Withdrawn
- 2017-06-15 CN CN201780050316.3A patent/CN109563743A/en active Pending
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|---|---|---|---|---|
| US3861822A (en) * | 1974-02-27 | 1975-01-21 | Gen Electric | Duct with vanes having selectively variable pitch |
| US5056738A (en) * | 1989-09-07 | 1991-10-15 | General Electric Company | Damper assembly for a strut in a jet propulsion engine |
| US20050042083A1 (en) * | 2003-07-09 | 2005-02-24 | Milburn Richard G. | Guide vane |
| US20120291449A1 (en) * | 2007-08-01 | 2012-11-22 | United Technologies Corporation | Turbine Section of High Bypass Turbofan |
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Also Published As
| Publication number | Publication date |
|---|---|
| CA3033186A1 (en) | 2018-02-22 |
| US20180045221A1 (en) | 2018-02-15 |
| EP3497306A1 (en) | 2019-06-19 |
| WO2018034729A1 (en) | 2018-02-22 |
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Application publication date: 20190402 |