CN208456919U - A kind of compressor inlet guide vane structure with the anti-icing function of gas heat - Google Patents
A kind of compressor inlet guide vane structure with the anti-icing function of gas heat Download PDFInfo
- Publication number
- CN208456919U CN208456919U CN201820783997.6U CN201820783997U CN208456919U CN 208456919 U CN208456919 U CN 208456919U CN 201820783997 U CN201820783997 U CN 201820783997U CN 208456919 U CN208456919 U CN 208456919U
- Authority
- CN
- China
- Prior art keywords
- guide vane
- compressor inlet
- inlet guide
- flows
- blade
- 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.)
- Active
Links
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The utility model provides a kind of compressor inlet guide vane structure with the anti-icing function of gas heat, it is arranged inside blade and individually opens up to main channel and multiple flow to subchannel, it flows to subchannel to communicate near blade trailing edge with blade suction surface, high-temperature gas is opened up to main channel and blended with subchannel inflow compressor sprue is flowed to.Specific structure includes: the guide blade sleeve of the up-front entry guide vane of removal and removal trailing edge, arranges that multiple even depth flow to groove along guide vane suction surface.The two is assembled to form exhibition to main channel, flows to groove and is exported as subchannel, uncovered area is flowed to as high-temperature gas by guide blade sleeve overlay area, and high-temperature gas is opened up to main channel and blended with flowing to groove and enter compressor sprue.The utility model can be extended to the air being evenly heated between compressor inlet guide vane and first order movable vane, and influence very little to the internal flow of compressor.
Description
Technical field
The utility model relates to gas-turbine unit design fields, and in particular to a kind of gas heat of compressor inlet guide vane
Ice prevention structure.
Background technique
For gas-turbine unit when high-altitude or cold zone work, engine inlet temperature is lower, even if environment temperature
When degree is higher than zero degree, the equally possible icing of engine inlets.Engine inlets freeze, and refer mainly to air intake duct leading edge, rectification
Cover, supporting plate and compressor inlet guide vane etc. freeze.
Air-flow is expanded in engine inlets to be accelerated, and be will lead to gas flow temperature decline and is frozen.When compressor use across sound/
When Supersonic blade profile, the expansion of edge region accelerates air-flow in front of the blade, equally exists the possibility of icing.Air-flow is compressed by compressor
Afterwards, temperature increases, and compressor later stages turn static component and will not usually freeze.
It freezes and seriously affects the normal work of engine.Air intake duct, which freezes, can change the shape of airflow channel, and reduction is started
Machine air inlet area, causes inlet flow field to distort.Under engine luggine effect, layers of ice may shed into compressor and damage
Hurt engine component, causes involuntary stoppage.Compressor rotor icing can change blade profile and blade is made to deviate design work state,
Lead to blade profile flow separation and makes compressor stall.
The anti-icing work of engine is most important, and the maintenance of gas thermal anti-icing system is simple, and reliable operation is answered extensively
With.The anti-icing gas heat of engine is exactly using hot air engine to protection coating, so that super-cooling waterdrop be avoided to freeze
It freezes.
Existing gas thermal anti-icing system mostly uses greatly the mode of high-temperature gas indirect heating compressor mainstream, first by high-temperature gas
Hollow guide vane is heated, then compressor mainstream is heated by hollow guide vane, anti-icing effect is limited.
Utility model content
For the disadvantages mentioned above and deficiency of the prior art, for the anti-icing need for meeting compressor inlet guide vane and first order movable vane
It asks, the utility model provides a kind of hot ice prevention structure of gas of compressor inlet guide vane, arranges and is individually opened up to main logical inside blade
Road and it is multiple flow to subchannel, respectively flow to subchannel and communicated near blade trailing edge with blade suction surface, high-temperature gas opened up to
It main channel and flows to subchannel and enters compressor sprue and blended, to improve anti-icing effect.
The technical scheme adopted by the utility model for solving the technical problem is:
A kind of compressor inlet guide vane structure with the anti-icing function of gas heat, including compressor inlet guide vane and guide blade sleeve,
It is characterized in that,
The leading edge edge of the compressor inlet guide vane is obliquely partially cut off by flow direction excision face, and at least retains the pressure
Leading edge at mechanism of qi entry guide vane leaf top and/or at blade root, and leading edge flows to excision face and is located at described calm the anger in chordwise location
The upstream of the blade profile maximum gauge of machine entry guide vane,
Extended on the suction surface of the compressor inlet guide vane to interval open up it is several flow to groove, and it is each it is described flow to it is recessed
The upstream boundary of slot is opened up to excision face with the leading edge and is smoothly transitted, and downstream boundary is close with the trailing edge of the compressor inlet guide vane
Like parallel；
The guide blade sleeve is the hollow blade profile for being set in compressor inlet guide vane outer surface,
The trailing edge of the suction surface of the guide blade sleeve flows to excision face in chordwise location by flow direction excision face complete resection, trailing edge
Above between each upstream and downstream boundary for flowing to groove,
The trailing edge of the guide blade sleeve pressure face is by flow direction excision face complete resection, and the trailing edge flows to excision face tangential
Positioned at the downstream of the blade profile maximum gauge of the guide blade sleeve on position；
The guide blade sleeve is set in after compressor inlet guide vane outer surface, and each groove that flows to is by the guide vane
Set partly covers, and each capped region of groove that flows to is formed as flowing to subchannel, and uncovered region is formed as
High-temperature gas outlet, space between the compressor inlet guide vane and the guide blade sleeve are formed as one in edge and extend to prolonging
Stretch and with it is each it is described flow to exhibition that subchannel is connected to main channel,
Described open up to the end of main channel is equipped with high-temperature gas entrance, and the high-temperature gas enters through described open up to main channel
It is each it is described flow to subchannel, and enter in compressor sprue along each high-temperature gas outlet.
Preferably, each groove that flows to extends on the suction surface that the compressor inlet guide vane is arranged at equal intervals.
Preferably, the guide blade sleeve is the hollow blade profile of equal thickness, the blade profile of inner surface and the compressor inlet guide vane
Identical, the two can be bonded completely.
Preferably, in the compressor inlet guide vane, it is plane or the surface of revolution, leading edge stream that leading edge, which is opened up to excision face,
It is clinoplain or complex-curved to excision face.
Preferably, the high-temperature gas entrance setting is at the compressor inlet guide vane leaf top or at blade root.
Further, for ensure high-temperature gas evenly distribute to it is each it is described flow to groove, when the high-temperature gas entrance is set
When setting at the blade root of the compressor inlet guide vane, the leaf top leading edge of the compressor inlet guide vane is not cut off, leading edge excision
Region is radially gradually reduced.
When further, at the leaf top that the compressor inlet guide vane is arranged in the high-temperature gas entrance, the pressure
The blade root leading edge of mechanism of qi entry guide vane is not cut off, and leading edge cut-away area is radially gradually increased.
Preferably, each groove arrangement that flows to respectively flows to the depth phase of groove in the different leaf eminences of guide vane suction surface
Together, of same size or not identical.
It further, can be appropriate to guarantee heating effect of the high-temperature gas at the leaf top of the compressor inlet guide vane
Increase the width for flowing to groove at leaf top, that is, the width for flowing to groove being located at leaf top is recessed greater than flowing to for other leaf eminences
The width of slot.
Preferably, for the trailing edge of the suction surface of the guide blade sleeve by flow direction excision face complete resection, excision face is clinoplain
Or it is complex-curved, and trailing edge flows to the trailing edge less parallel in excision face Yu the compressor inlet guide vane.
Preferably, in order to assemble needs, the trailing edge of the pressure face of the guide blade sleeve is by flow direction excision face complete resection, excision
Face is clinoplain or complex-curved, and trailing edge flows to excision face in chordwise location positioned at the blade profile maximum of the guide blade sleeve
The downstream of thickness.
Compared with the existing technology, the compressor inlet guide vane structure with the anti-icing function of gas heat of the utility model, passes through
Exhibition is opened up inside blade to main channel and subchannel is flowed to, flow to subchannel near blade trailing edge with blade suction surface phase
Logical, high-temperature gas is opened up to main channel and is blended with subchannel inflow compressor sprue is flowed to, and can be extended and be added to uniform
Air between hot pressing mechanism of qi entry guide vane and first order movable vane, and very little is influenced on compressor internal flow.
Detailed description of the invention
Fig. 1 is the schematic diagram of the compressor inlet guide vane with the anti-icing function of gas heat of the utility model；
Fig. 2 is the structural schematic diagram for removing up-front compressor inlet guide vane；
Fig. 3 is the structural schematic diagram for removing the guide blade sleeve of trailing edge；
Fig. 4 is the compressor inlet guide vane assembling schematic diagram with the anti-icing function of gas heat of the utility model；
Fig. 5 is the B-B direction cross-sectional view of Fig. 4；
Fig. 6 is the C-C of Fig. 4 to cross-sectional view；
Marginal data
1. high-temperature gas entrance；2. opening up to main channel；3. flowing to subchannel；4. high-temperature gas exports；5. compressor inlet
Guide vane；6. flowing to groove；7. guide vane is up-front to flow to excision face；It opens up 8. guide vane is up-front to excision face；9. removal trailing edge is led
Leaf set；10. the trailing edge of guide blade sleeve suction surface flows to excision face；11. the trailing edge of guide blade sleeve pressure face flows to excision face；12. flow direction
The upstream boundary of groove；13. flowing to the downstream boundary of groove.
Specific embodiment
The utility model is described in detail with reference to the accompanying drawing, it is noted that described specific embodiment is only
It is intended to convenient for the understanding to the utility model, and does not play any restriction effect to it.
As shown in Figure 1, the compressor inlet guide vane structure with the anti-icing function of gas heat of the utility model, using blade root or
Leaf top intake method (shows leaf top intake method) in Fig. 1, including the up-front trough of belt compressor inlet guide vane 5 of removal and removal
The guide blade sleeve 9 of trailing edge, the two are assembled to form exhibition to main channel 2, wherein flowing to groove 6 by 9 overlay area of guide blade sleeve as flow direction
Subchannel 3, uncovered area is as high-temperature gas outlet 4.High-temperature gas is opened up to main channel 2 and is calmed the anger with the entrance of groove 6 is flowed to
Owner's runner blends.
As shown in Fig. 2, the leading edge of compressor inlet guide vane 5 is obliquely partially cut off by flow direction excision face, and at least retain
Leading edge at 5 leaf top of compressor inlet guide vane and/or at blade root (leading edge at figure middle period top is not removed).Leading edge flow direction excision
Face 7 is clinoplain or complex-curved, and leading edge flows to excision face 7 and is located on guide vane blade profile maximum gauge in chordwise location
Trip.It is plane that leading edge, which is opened up to excision face 8, apart from 7.5% leaf of leaf top height.In Fig. 2, in order to ensure high-temperature gas is evenly distributed to each
Groove 6 is flowed to, leading edge cut-away area is radially gradually reduced, and wherein leading edge flows to excision face 7 before blade root positional distance guide vane
The axial chord length of edge 33%, and leading edge flows to excision face 7 in the axial chord length of leaf top positional distance guide vane leading edge 18%.Correspondingly, when
When leading edge at blade root is not removed, leading edge cut-away area is radially gradually increased.
As shown in Fig. 2,5,6, compressor inlet guide vane 5 is equal deep along high position arranged for interval 7, guide vane suction surface difference leaf
Degree flows to groove 6, and the groove depth for respectively flowing to groove 6 is 0.3mm, and opening up to spacing is 3.5mm.Disleaf top flows to outside groove, each to flow
It is 4mm to the width of groove.It flows to the upstream boundary 12 of groove 6 and guide vane leading edge flows to excision face 7 and smoothly transits, flow to recessed
The downstream boundary 13 and guide vane trailing edge less parallel of slot 6, the downstream boundary 13 for flowing to groove 6 are axial apart from blade trailing edge about 15%
Chord length.In order to guarantee high-temperature gas in the heating effect of leaf top zone, increases leaf top zone and flow to the width of groove 6 to 6mm.
As shown in Fig. 3,5,6, guide blade sleeve 9 be the hollow blade profile of equal thickness, guide blade sleeve 9 with a thickness of 0.4mm.Guide blade sleeve 9
Inner surface is identical as the blade profile of compressor inlet guide vane 5, and the two can be bonded completely.The trailing edge of 9 suction surface of guide blade sleeve, which is flowed to, to be cut
Except face complete resection, it is clinoplain that trailing edge, which flows to excision face 10, and trailing edge flows to excision face 10 in chordwise location positioned at all
It flows between the upstream boundary 12 of groove 6 and downstream boundary 13, and is located at the downstream of the blade profile maximum gauge of guide blade sleeve 9, trailing edge
The trailing edge less parallel in the excision face of flow direction 10 and compressor inlet guide vane 5, trailing edge cut off face 10 apart from about 38% axis of blade trailing edge
To chord length.In order to assemble needs, the part trailing edge of 9 pressure face of guide blade sleeve is cut off, trailing edge excision face 11 is for clinoplain or again
Miscellaneous curved surface, trailing edge flow to the downstream of blade profile maximum gauge of the excision face 11 positioned at 50% axial chord length nearby and positioned at guide blade sleeve 9.
As shown in Fig. 1,4~6, the compressor inlet guide vane structure with the anti-icing function of gas heat of the utility model, by going
Except the guide blade sleeve 9 of up-front trough of belt compressor inlet guide vane 5 and removal trailing edge is assembled.Guide blade sleeve 9 be set in compressor into
It after 5 outer surface of mouth guide vane, respectively flows to groove 6 and is partly covered by guide blade sleeve 9, respectively flow to the capped region of groove and be formed as
Flow to subchannel 3, uncovered region is formed as high-temperature gas outlet 4, compressor inlet guide vane 5 and the guide blade sleeve 9 it
Between space be formed as one in edge and extend to extending and flowing to exhibition that subchannel 3 be connected to main channel 2 with each, open up and lead to main
The end in road 2 is equipped with high-temperature gas entrance 1, high-temperature gas opened up to main channel 2 enter it is each it is described flow to subchannel 3, and along
Each high-temperature gas outlet 4, which enters in compressor sprues, to be blended, can extend to be evenly heated compressor inlet guide vane with
Air between first order movable vane, and very little is influenced on compressor internal flow.
The range of the above, the only preferred embodiment of the utility model, the utility model protection is not limited thereto,
Any people for being familiar with the technology is appreciated that that expects transforms or replaces in the range disclosed by the utility model, should all cover
Within the scope of the utility model, therefore, the protection scope of the utility model should be with the protection scope of claims
Subject to.
Claims (10)
1. a kind of compressor inlet guide vane structure with the anti-icing function of gas heat, including compressor inlet guide vane and guide blade sleeve,
It is characterized in that,
The leading edge of the compressor inlet guide vane is obliquely partially cut off by flow direction excision face, and at least retain the compressor into
Leading edge at mouth guide vane leaf top and/or at blade root, and leading edge flows to excision face and is located at the compressor inlet in chordwise location
The upstream of the blade profile maximum gauge of guide vane,
Extended on the suction surface of the compressor inlet guide vane to interval open up it is several flow to groove, and each groove that flows to
Upstream boundary flows to excision face with the leading edge and smoothly transits, and downstream boundary is approximate with the trailing edge of the compressor inlet guide vane flat
Row；
The guide blade sleeve is the hollow blade profile for being set in compressor inlet guide vane outer surface,
The trailing edge of the suction surface of the guide blade sleeve is by flow direction excision face complete resection, and trailing edge flows to excision face in chordwise location
Positioned at it is each it is described flow between the upstream boundary of groove and downstream boundary,
The trailing edge of the pressure face of the guide blade sleeve is by flow direction excision face complete resection, and trailing edge flows to excision face in chordwise location
Positioned at the downstream of the blade profile maximum gauge of the guide blade sleeve；
The guide blade sleeve is set in after compressor inlet guide vane outer surface, and each groove that flows to is by the guide blade sleeve portion
Divide ground covering, each capped region of groove that flows to is formed as flowing to subchannel, and uncovered region is formed as high temperature
Gas vent, the space between the compressor inlet guide vane and the guide blade sleeve are formed as one in edge and extend to extension simultaneously
With it is each it is described flow to exhibition that subchannel is connected to main channel,
Described open up to the end of main channel is equipped with high-temperature gas entrance, and the high-temperature gas enters each institute through described open up to main channel
It states and flows to subchannel, and entered in compressor sprue by each high-temperature gas outlet.
2. compressor inlet guide vane structure according to claim 1, which is characterized in that it is each it is described flow to groove extend to etc.
It is arranged at intervals on the suction surface of the compressor inlet guide vane.
3. compressor inlet guide vane structure according to claim 1, which is characterized in that the guide blade sleeve is that equal thickness is hollow
Blade profile, inner surface is identical as the blade profile of the compressor inlet guide vane, and the two can be bonded completely.
4. compressor inlet guide vane structure according to claim 1, which is characterized in that in the compressor inlet guide vane,
It is that perhaps its complex-curved leading edge flows to excision face to clinoplain is plane or the surface of revolution that its leading edge, which flows to excision face,.
5. compressor inlet guide vane structure according to claim 1, which is characterized in that the high-temperature gas entrance setting exists
At the leaf top of the compressor inlet guide vane or at blade root.
6. compressor inlet guide vane structure according to claim 5, which is characterized in that when the high-temperature gas entrance is arranged
When at the blade root of the compressor inlet guide vane, the leaf top leading edge of the compressor inlet guide vane is not removed, leading edge excision
Region is radially gradually reduced.
7. compressor inlet guide vane structure according to claim 5, which is characterized in that when the high-temperature gas entrance is arranged
When at the leaf top of the compressor inlet guide vane, the blade root leading edge of the compressor inlet guide vane is not removed, leading edge excision
Region is radially gradually increased.
8. compressor inlet guide vane structure according to claim 1, which is characterized in that each groove arrangement that flows to is in institute
The different leaf eminences of compressor inlet guide vane suction surface are stated, each depth for flowing to groove is identical, of same size or not identical.
9. compressor inlet guide vane structure according to claim 8, which is characterized in that described at leaf top flows to recessed
The width of slot is greater than the width for flowing to groove of other leaf eminences.
10. compressor inlet guide vane structure according to claim 1, which is characterized in that the suction surface of the guide blade sleeve
Trailing edge is by flow direction excision face complete resection, and it is clinoplain or complex-curved that trailing edge, which flows to excision face, and the trailing edge flows to
The trailing edge less parallel in excision face and the compressor inlet guide vane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820783997.6U CN208456919U (en) | 2018-05-24 | 2018-05-24 | A kind of compressor inlet guide vane structure with the anti-icing function of gas heat |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820783997.6U CN208456919U (en) | 2018-05-24 | 2018-05-24 | A kind of compressor inlet guide vane structure with the anti-icing function of gas heat |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208456919U true CN208456919U (en) | 2019-02-01 |
Family
ID=65149056
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820783997.6U Active CN208456919U (en) | 2018-05-24 | 2018-05-24 | A kind of compressor inlet guide vane structure with the anti-icing function of gas heat |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208456919U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108591123A (en) * | 2018-05-24 | 2018-09-28 | 中国科学院工程热物理研究所 | A kind of compressor inlet guide vane structure with the anti-icing function of gas heat |
-
2018
- 2018-05-24 CN CN201820783997.6U patent/CN208456919U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108591123A (en) * | 2018-05-24 | 2018-09-28 | 中国科学院工程热物理研究所 | A kind of compressor inlet guide vane structure with the anti-icing function of gas heat |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US4859147A (en) | Cooled gas turbine blade | |
| CN1936526B (en) | Total air temperature probe having improved deicing heater error performance | |
| US20140010650A1 (en) | Tip leakage flow directionality control | |
| CN104196574B (en) | A kind of gas combustion turbine cooling blade | |
| EP0709550A1 (en) | Cooled shroud | |
| US4720235A (en) | Turbine engine with induced pre-swirl at the compressor inlet | |
| EP3090132B1 (en) | Gas turbine engines and corresponding method | |
| JP5415532B2 (en) | Air injection into the turbomachine compressor flow path | |
| CN105888850B (en) | A kind of vane type preswirl nozzle with rectification rib | |
| US20150330230A1 (en) | Tip leakage flow directionality control | |
| US20180202297A1 (en) | Tip leakage flow directionality control | |
| KR101885402B1 (en) | Gas turbine diffuser blowing method and corresponding diffuser | |
| CN107532515A (en) | Compressor stage | |
| CN205669438U (en) | A kind of vane type preswirl nozzle structure of band rectification rib | |
| CN106968722B (en) | Turbine airfoil trailing edge cooling passage | |
| CN107060893A (en) | A kind of turbine blade tail flow-disturbing with V-type rib partly splits seam cooling structure | |
| CN208456919U (en) | A kind of compressor inlet guide vane structure with the anti-icing function of gas heat | |
| CN107269319A (en) | A kind of turbine blade tail flow-disturbing with sphere pit partly splits seam cooling structure | |
| US10337333B2 (en) | Turbine blade comprising a central cooling duct and two side cavities connected downstream from the central duct | |
| CN104088704B (en) | A kind of have the aeroengine hot air anti-icing chamber device conformal with anti-icing wall | |
| CN108591123A (en) | A kind of compressor inlet guide vane structure with the anti-icing function of gas heat | |
| US3365124A (en) | Compressor structure | |
| CN207333296U (en) | Gas-turbine unit | |
| CN203547922U (en) | Shunt ring, engine anti-icing device and turbofan engine | |
| CN112780442B (en) | Adjustable runner ramjet engine and design and adjustment method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20210918 Address after: 251401 room A107, Cuizhai business center, No. 1, central street, Cuizhai street, Jiyang District, Jinan City, Shandong Province Patentee after: Jinan Zhongke Xianxian Gas Turbine Technology Co.,Ltd. Address before: 100190, No. 11 West Fourth Ring Road, Beijing, Haidian District Patentee before: Institute of Engineering Thermophysics, Chinese Academy of Sciences |
|
| TR01 | Transfer of patent right |