CN102400956A - Method and apparatus for air flow control - Google Patents
Method and apparatus for air flow control Download PDFInfo
- Publication number
- CN102400956A CN102400956A CN2011102802287A CN201110280228A CN102400956A CN 102400956 A CN102400956 A CN 102400956A CN 2011102802287 A CN2011102802287 A CN 2011102802287A CN 201110280228 A CN201110280228 A CN 201110280228A CN 102400956 A CN102400956 A CN 102400956A
- Authority
- CN
- China
- Prior art keywords
- stator
- shape
- memory material
- air stream
- rotor
- 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
Images
Classifications
-
- 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
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/02—Selection of particular materials
- F04D29/023—Selection of particular materials especially 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
- F05D2300/133—Titanium
-
- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/16—Other metals not provided for in groups F05D2300/11 - F05D2300/15
-
- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/50—Intrinsic material properties or characteristics
- F05D2300/505—Shape memory behaviour
-
- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/603—Composites; e.g. fibre-reinforced
-
- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/614—Fibres or filaments
Abstract
The invention relates to a method and an apparatus for air flow control. According to one aspect of the invention, an air flow control apparatus includes a guide vane to be positioned between an air inlet and a rotor of a turbomachine. Further, the guide vane includes a geometry configured to control an air flow incidence on the rotor, the guide vane further having a substantially constant aspect ratio. In addition, a body of the guide vane includes a shape memory material configured to change a geometry of the guide vane in response to energy provided by a power source.
Description
Technical field
Theme disclosed herein relates to gas turbine.More specific, this theme relates to the stator in gas turbine.
Background technique
In gas turbine, compressor adds kinetic energy to the fluid such as air through the tangential momentum that increases fluid.Flow to turbine from the kinetic energy of compressor with from the heat energy of burner by fluid (usually being air), the energy of fluid is converted into mechanical energy in turbine.Some factors can influence the efficient of in compressor, adding kinetic energy.These factors can be included in the interior air distribution of compressor, stride across the pressure liter and the loss source in compressor of compressor.An embodiment is the stator in compressor, and its influence gets into the distribution and the amplitude of the air stream in the compressor.Stator can be designed under the selected operating mode (output of high power and/or high firing rate for example at full capacity) at turbine high efficient is arranged.Air stream in the stator control compressor, this has determined to be supplied to the giving of kinetic energy (entitlement) of the remaining part of combustion gas turbine systems.But, when with the power of lower load and minimizing output operation, load from the air flow distribution and the aerodynamics of stator and to cause having the gas turbine performance of poor efficiency.
Summary of the invention
According to an aspect of the present invention, a kind of air stream control apparatus comprises the stator between air inlet that is positioned turbo machine and the compressor drum.In addition, this stator comprises the geometrical shape that is configured to control epitrochanterian air stream incident, and this stator also has the aspect ratio of substantial constant.In addition, the main body of stator comprises the shape-memory material that is configured to change in response to the energy that is provided by power supply the geometrical shape of stator.
According to a further aspect in the invention, a kind of method that is used for controlling the air stream of compressor comprises: the air from inlet is flowed towards stator; And the shape-memory material in the stator applied energy, control distribution with the geometrical shape that changes stator towards the air stream of rotor.
According to another aspect of the invention, a kind of turbocompressor comprises air inlet, is positioned the rotor in the downstream of air inlet, and is positioned the stator between air inlet and the rotor, and this stator comprises shape-memory material.This compressor also comprises the power supply that is connected on the shape-memory material to cause the stator geometrical shape to change.
According to the following description that combines accompanying drawing to obtain, these will become more obvious with other advantage and characteristic.
Description of drawings
In the claim at the conclusion part place of specification, point out especially and require protection to be counted as theme of the present invention clearly.According to the following detailed description that combines accompanying drawing to obtain, aforementioned and further feature and advantage of the present invention are conspicuous, wherein:
Fig. 1 is an embodiment's the side cross-sectional view that comprises the gas turbine of the compressor with stator and rotor;
Fig. 2 is the sectional view of the stator of Fig. 1;
Fig. 3 is into an embodiment's the sectional view of stator of the shape of aerofoil profile part; And
Fig. 4 is an embodiment's of the stator when shape-memory material changes the stator geometrical shape a perspective view.
Detailed description has been set forth embodiments of the invention with the mode with reference to the instance of accompanying drawing, and advantage and characteristics.
List of parts:
100 gas turbines
102 axis
104 stators
106 compressors
Hub in 108
110 shells
112 entrance regions
114 air streams
116 rotors
118 stators
120 rotors
122 stators
124 rotors
126 stators
128 streams
130 power supplys
132 controllers
134 strings
136 length
200 aerofoil profile parts
202 leading edges
204 trailing edges
206 aerofoil profile part walls
208 leads
210 cavitys
300 aerofoil profile parts
302 leading edges
304 trailing edges
306 aerofoil profile part walls
308 leads
310 cavitys
400 stators
402 first shapes
404 second shapes
406 rotations
408 stator blade roots
410 stator blade tips
Embodiment
Fig. 1 has shown an embodiment's of the gas turbine 100 that is provided with around cener line 102 side cross-sectional view.This turbine 100 comprises the stator 104 that is arranged in the compressor 106.Air in compressor 106, be compressed and and fuel mix, fuel burns in burner and in turbine, expands.Turbine rotates in response to expansion then, thus Driven Compressor 106 and the output of generation rotating power.
A plurality of inlet guide vanes 104 (showing one) are arranged on the front of one or more compressors 106 around cener line 102.As describe, hub 108 and shell 110 in compressor 106 comprises, thus the air flow path towards one or more burners is provided.Inlet guide vane 104 will guide the first order to compressor 106 downstream from the air stream (indicated like arrow 114) of entrance region 112.On the one hand, compressor 106 comprises a plurality of levels.The first order in these a plurality of levels comprises rotor 116 and stator 118.Similarly, the second level comprises rotor 120 and stator 122, and the third level comprises rotor 124 and stator 126.Air stream 114 is towards downstream flow, and wherein, stator 104 produces through these a plurality of compressor stages and gets into flow distribution or the flow field in the burner, and it is by 128 indications of stray arrow head.
In one embodiment; Stator 104 (also being " inlet guide vane " or " IGV ") comprises shape-memory material (or " marmem "); This shape-memory material operationally is communicated with stator 104, when shape-memory material is applied energy, to change the geometrical shape of stator 104.For example, shape-memory material is embedded in inside and/or the outside of stator 104 or forms the inside and/or the outside part of stator 104.Shape-memory material can comprise flexible composite, and in this composite material, embedding has conductor or lead.Lead operationally is connected on the power supply 130, and wherein, power supply optionally applies the energy of the electric current and the form of heat to lead.On the one hand, power supply 130 is connected on the controller 132, to come based on the turbine operating mode lead is optionally applied electric current and change the geometrical shape of stator 104.Produce significant temperature variation when the transmission current such as the conductor material of NiTi (NiTi).In one embodiment, the straight NiTi lead that has a straight basically shape is wound in tight spiral and is embedded in the composite material.When lead was applied the electric current of selected level, lead was heated to keep its previous straight basically shape.Therefore, when current carrying conductor stretched, the compound shape memory material can become second shape or geometrical shape from first shape.Power supply 130 with the electric current of selected level from such as direct current (DC) source of battery, offer lead based on interchange (AC) source or any other suitable power supply of line of electric force.Shape-memory material can be described to have such shape-memory character: wherein, material is based on remember multiple different shape such as the situation of the energy that imposes on material.For example, shape-memory material is configured to have a kind of shape at the low temperature place and has second kind of shape at the high temperature place.Material in heating and cooling display shape memory character during both can be known as the bidirectional shape memory material.As describe, stator 104 is the aerofoil profile part that is limited string 134 and length 136 sizes, wherein, aspect ratio (length/string) is the expression of the relation of these sizes.In one embodiment, when the shape of stator or geometrical shape were changed by shape-memory material, the aspect ratio of stator 104 was substantial constant or fixing.
Continuation is referring to the embodiment of Fig. 1, and when the electric current of selected level was directed to the lead that embeds, stator 104 geometrical shapies can change.For example, the profile of stator 104 or geometrical shape are the form of second shape that designs to first shape that designs with the turbine operating mode of the power that increases at full capacity with to the load that reduces or reduction of speed (turn down) turbine operating mode.At full capacity operating mode comes across need be from the power of the increase of turbine the time, and low-load or reduction of speed operating mode came across during the off-peak hours when needing less power.Therefore, first form generation makes it possible under the full load operating mode, have the air flow distribution of improved burning, efficient and power production.Second form generation is for lower power regime (for example during the power demand of non-peak) air flow distribution the most efficiently.In every respect, when the radial distribution of air stream had been improved the uniformity through compressor, the turbine combustion efficiency was improved.Particularly, cause when air stream incident is uniformly basically arranged on rotor blade under the multiple turbine load condition at the geometry-variable of stator 104, total efficiency is improved.Air stream incident is from the relation of the air stream of stator and rotor blade or aligning degree.Basically uniformly the air stream turbine operating mode that causes that can be described as be on the span of aerofoil profile part (stator or rotor blade) has the radial air of improved efficient to distribute.In one embodiment, stator 104 change stators with respect to angle from the air stream of inlet, this depends on the turbine operating mode.In addition, efficient also receives the influence of the amount of the air stream through compressor 100.The amount of air stream depends on the amount that is ejected into the fuel in the burner and the turbine load condition that is associated and different.In every respect, different power provides different operating conditionss with the firing rate situation, and wherein, the geometry-variable of regulating stator 104 improves turbine efficiency.In one embodiment, stator 104 comprises single parts or part.In other embodiments, stator 104 comprises a plurality of parts.
In certain embodiments, the total of stator 104 comprises shape-memory material, and wherein, lead is embedded in the whole structure based on composite material.Such structure allows the whole geometrical shape of stator 104 to change based on current working.In other embodiments, the selected part or the zone of stator 104 structures comprise shape-memory material.For example, the trailing edge of stator 104 comprises shape-memory material, thereby makes the profile of trailing edge or geometrical shape optionally to change based on the turbine operating mode.In another embodiment, leading edge is based on the electric current of the shape-memory material that optionally imposes on the leading edge that is arranged in stator and change geometrical shape.In every respect, the shape-memory material of stator 104 comprises alloy, flexible carbon fiber composite, lead and/or nano particle, and wherein, when energy imposed on the selected part of this material or material, shape-memory material can change shape.The energy that imposes on material can comprise electric current, voltage, electromagnetic wave, heat or other suitable energy.Although about the gas turbine engine 100 of particular type and shown the stator 104 of present embodiment, this stator can be used for any known turbogenerator type, includes but not limited to that steamturbine, gas turbine and boat change turbine.Notice that in certain embodiments the air stream of being described that passes through compressor 106 comprises any suitable fluid, comprise air, oxygen, gaseous fuel, liquid fuel or their any combination.In addition, the stator 104 of geometry-variable can be positioned between each level of compressor 106.As discussed herein, stator 104 also is known as the air stream control apparatus.
Fig. 2 is that it illustrates into the profile of the stator 104 of aerofoil profile part 200 shapes along the sectional view of the line 2-2 institute intercepting of Fig. 1.Aerofoil profile part 200 comprises leading edge 202 and trailing edge 204.Aerofoil profile part 200 comprises the shape-memory material of at least a portion that forms aerofoil profile part wall 206, for example flexible composite.Conductor such as lead 208 is embedded in the aerofoil profile part wall 206.As describe, therefore lead 208 is embedded in the flexible composite wall 206 of trailing edge 204, forms trailing edge shape-memory zone.In one embodiment, aerofoil profile part 200 is essentially hollow structure, and wherein, cavity 210 is surrounded by aerofoil profile part wall 206.Like previous discussion, when lead 208 is applied electric current, comprise that the shape-memory material of composite walls 206 and lead 208 can change the geometrical shape of trailing edge 204.In certain embodiments, shape-memory material and aerofoil profile part 200 change geometrical shape based on the time in one day, and wherein, the time is corresponding to the power output of operating mode and expectation.For example, the turbogenerator of supposing is from 8PM to 8AM experience running on the lower load and from 8AM to 8PM experience full load operating mode.Therefore; Aerofoil profile part 200 have be designed to first shape that improved efficient is arranged under the full load operating mode be designed under running on the lower load, have second shape of improved efficient; Wherein, the change of shape material makes it possible to the variation between first shape and second shape.In one embodiment; The controller that comprises processor, storage, software, firmware, input and output is connected on the power supply, changes with the geometrical shape of controlling corresponding to operating mode that arrange or programming in advance (low load time and full load time that example is as discussed above).In another embodiment, feedback loop moves on controller 132, and this feedback loop receives the turbine parameter that senses, and wherein, the turbine parameter that usage measures is confirmed the geometrical shape of aerofoil profile part 200.For example, sensor is confirmed temperature and the amount of undesirable combustion by-products in the burner.Therefore, temperature that senses and by product parameter are used for confirming the improved aerofoil profile part and the stator geometrical shape of the turbo-power production of the operating mode that is used to sense, and the current corresponding level is sent to shape-memory material.In an embodiment, shape-memory material changes aerofoil profile part 200 geometrical shapies in one or more dimensions or zone and/or whole stator profile.For example, shape-memory material becomes to make stator that the expansion and the contraction of spanwise and/or chord line are arranged with wire configurations.In addition, shape-memory material is configured to make at least a portion rotation of stator.For example, lead is embedded in the aerofoil profile part wall, thereby causes the span variation of stator blade tip and cause the fixedly blade root rotation of stator blade tip around stator.
Fig. 3 is into an embodiment's the sectional view of stator of the shape of aerofoil profile part 300.Aerofoil profile part 300 comprises leading edge 302 and trailing edge 304.Aerofoil profile part 300 comprises aerofoil profile part wall 306, and wherein, at least a portion of wall 306 comprises shape-memory material.Shape-memory material comprises the leading edge lead 308 and trailing edge lead 309 in the flexible composite that is embedded in aerofoil profile part wall 306.Aerofoil profile part 300 is essentially hollow, has cavity 310, thereby provides flexible to the aerofoil profile part.Therefore, aerofoil profile part 300 geometrical shapies can change when the flexible shape memory material to wall applies energy.As describe, leading edge lead 308 is embedded in the wall 306 with trailing edge lead 309, thus in the leading edge portion and rear edge part (302,304) of aerofoil profile part 300 formation shape-memory district among both.Therefore,, leading edge lead 308 and/or trailing edge lead 309 are applied selected electric current, change of shape is arranged to make leading edge 302 and/or trailing edge 304 respectively based on the turbine operating mode.Therefore, in certain embodiments, for multiple turbine load condition, the shape-memory material in stator 300 makes can have air stream incident uniformly basically on the rotor blade.Basically incident uniformly causes along spanwise uniform radial air flow distribution being arranged on rotor blade, and wherein, incident uniformly causes under selected turbine load condition, improved compressor and combustor efficiency being arranged basically.In addition, be designed to have under a kind of operating mode improved burning with efficient but the static stator geometrical shape that efficient is lower under second kind of operating mode compare, the shape-memory material in stator 300 provides improved total turbine efficiency.
Fig. 4 is an embodiment's of stator 400 a perspective view.Stator 400 is illustrated and is in first shape 402 and second shape 404.As discussed above, the shape-memory material in stator 400 makes can have geometrical shape to change when shape-memory material being applied the energy of current forms.In one embodiment, shape or geometrical shape change makes stator 400 rotations, as indicated by arrow 406.In order to help to rotate 406, stator blade root 408 or stator blade tip 410 are attached on the compressor.For example, if stator blade root 408 is attached on inwall, hub or the housing of compressor, then when the change of shape material was applied electric current, stator blade tip 410 can be with respect to blade root 408 rotations 406.Perhaps blade root 408 or blade tip 410 are attached to and make blade root 408 and/or blade tip 410 relatively to rotate 406 on the compressor, and be as shown in Figure 4.When being in first shape 402 and under running on the lower load, being in second shape 404 under the full load operating mode, being rotated in of stator 400 provides improved air stream incident on the rotor.In an embodiment, the shape of stator 400 is different from the aerofoil profile part.In the embodiment with alternative stator shape, change of shape material and stator 400 are configured to based on operating mode geometrical shape changed, to improve turbine efficiency.
Though only combined the embodiment of limited quantity to describe the present invention in detail, should understand easily, the present invention is not limited to so disclosed embodiment.On the contrary, can revise the present invention with do not describe before combining but modification, the change of any amount suitable, substitute or equivalent arrangements with the spirit and scope of the present invention.In addition, though various embodiments of the present invention has been described, should be appreciated that each side of the present invention can comprise among the described embodiment more only.Therefore, the description restriction that the present invention should not be regarded as being undertaken by the front, but only by the scope restriction of accompanying claims.
Claims (10)
1. air stream control apparatus comprises:
Can be positioned the air inlet (112) of turbo machine (100) and the stator (104) between the rotor (116); Said stator (104) has the geometrical shape that is configured to control the air stream incident on the said rotor (116); Said stator also has the aspect ratio of substantial constant, and the main body of said stator comprises the shape-memory material that is configured to change in response to the energy that is provided by power supply (130) geometrical shape of said stator (104) at least in part.
2. equipment according to claim 1 is characterized in that, comes said shape-memory material is applied said energy based on the turbine load condition.
3. equipment according to claim 1 and 2 is characterized in that, said stator (104) comprises that individual construction and said stator geometrical shape comprise leading edge (202) and trailing edge (204).
4. equipment according to claim 3 is characterized in that, said shape-memory material comprises that the part of said trailing edge (204) and the shape that is configured to change said trailing edge (204) are to control the air stream incident on the said rotor (116).
5. equipment according to claim 3 is characterized in that, said shape-memory material comprises that the part of said leading edge (202) and the shape that is configured to change said leading edge (202) are to control the air stream incident on the said rotor (116).
6. method that is used for controlling the air stream of compressor (106) comprises:
Air from inlet (112) is flowed towards stator (104); And
Shape-memory material in the said stator (104) applies energy, controls the incident of the air stream on the rotor (116) with the geometrical shape that changes said stator (104).
7. method according to claim 6 is characterized in that, applies energy and comprises that be second shape with the said geometrical shape of said stator (104) from first alteration of form based on the turbine load condition.
8. according to claim 6 or 7 described methods, it is characterized in that, said shape-memory material is applied energy comprise that the lead (208) to being embedded in the flexible composite applies electric current.
9. according to claim 6 or 7 described methods, it is characterized in that, apply energy and comprise making that air stream incident is uniformly arranged on the said rotor (116) basically based on operating mode.
10. according to claim 6 or 7 described methods, it is characterized in that, apply when said geometrical shape that energy is included in said stator (106) changes the blade root (408) of said stator (106) or blade tip (410) are moved.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US12/859707 | 2010-08-19 | ||
| US12/859,707 US20120045318A1 (en) | 2010-08-19 | 2010-08-19 | Method and apparatus for air flow control |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102400956A true CN102400956A (en) | 2012-04-04 |
Family
ID=45594219
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011102802287A Pending CN102400956A (en) | 2010-08-19 | 2011-08-19 | Method and apparatus for air flow control |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US20120045318A1 (en) |
| JP (1) | JP2012041929A (en) |
| CN (1) | CN102400956A (en) |
| CH (1) | CH703659A2 (en) |
| DE (1) | DE102011052597A1 (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103511083A (en) * | 2012-06-25 | 2014-01-15 | 通用电气公司 | Systems and methods to control flow in a rotor wheel |
| CN107315403A (en) * | 2016-04-27 | 2017-11-03 | 通用电气公司 | With the performance model control machinery of calibration |
| CN107725215A (en) * | 2016-08-11 | 2018-02-23 | 通用电气公司 | For the inlet guide vane component for the air stream swirl flow distortion for reducing aircraft aft-fan |
| CN109458362A (en) * | 2017-09-06 | 2019-03-12 | 赛峰航空器发动机 | Reinforce the composite material casing of shape |
| CN110005640A (en) * | 2018-01-04 | 2019-07-12 | 中国航发商用航空发动机有限责任公司 | A kind of fan blade, compressor and aero-engine |
| CN110005641A (en) * | 2018-01-04 | 2019-07-12 | 中国航发商用航空发动机有限责任公司 | Compressor blade and compressor flow separation control method |
Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102012222230A1 (en) * | 2012-12-04 | 2014-06-05 | Pfeiffer Vacuum Gmbh | vacuum pump |
| EP3249205B1 (en) * | 2015-05-27 | 2020-01-29 | IHI Corporation | Jet engine |
| GB201509707D0 (en) * | 2015-06-04 | 2015-07-22 | Rolls Royce Plc | An actuation arrangement |
| US10352173B2 (en) | 2016-03-02 | 2019-07-16 | United Technologies Corporation | Shape memory alloy variable stiffness airfoil |
| BE1024699B1 (en) * | 2016-10-26 | 2018-06-01 | Safran Aero Boosters S.A. | LOW MEMORY PRESSURE COMPRESSOR FOR AXIAL TURBOMACHINE |
| US10428825B2 (en) * | 2016-11-14 | 2019-10-01 | United Technologies Corporation | Airfoil structure having a shape memory alloy actuator |
| US11028725B2 (en) | 2018-12-13 | 2021-06-08 | Raytheon Technologies Corporation | Adaptive morphing engine geometry |
| US11111811B2 (en) * | 2019-07-02 | 2021-09-07 | Raytheon Technologies Corporation | Gas turbine engine with morphing variable compressor vanes |
| CN112429196A (en) * | 2020-12-06 | 2021-03-02 | 西安长峰机电研究所 | Self-adaptive missile wing structure |
| US11821319B2 (en) | 2021-07-27 | 2023-11-21 | General Electric Company | Frangible airfoil with shape memory alloy |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2526409A (en) * | 1945-01-09 | 1950-10-17 | Lockheed Aircraft Corp | Turbo-propeller type power plant having radial flow exhaust turbine means |
| US6669444B2 (en) * | 2001-03-16 | 2003-12-30 | C.R.F. Societa Consortile Per Azioni | Fan or propeller, with shape memory |
| US20060140772A1 (en) * | 2004-12-24 | 2006-06-29 | Mcmillan Alison J | Composite blade |
| US20070110583A1 (en) * | 2005-09-24 | 2007-05-17 | Rolls-Royce Plc | Vane assembly |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2083174A1 (en) * | 2008-01-25 | 2009-07-29 | Siemens Aktiengesellschaft | Inlet guide vane for a gas compressor |
-
2010
- 2010-08-19 US US12/859,707 patent/US20120045318A1/en not_active Abandoned
-
2011
- 2011-08-11 DE DE102011052597A patent/DE102011052597A1/en not_active Withdrawn
- 2011-08-16 JP JP2011177792A patent/JP2012041929A/en not_active Withdrawn
- 2011-08-16 CH CH01342/11A patent/CH703659A2/en not_active Application Discontinuation
- 2011-08-19 CN CN2011102802287A patent/CN102400956A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2526409A (en) * | 1945-01-09 | 1950-10-17 | Lockheed Aircraft Corp | Turbo-propeller type power plant having radial flow exhaust turbine means |
| US6669444B2 (en) * | 2001-03-16 | 2003-12-30 | C.R.F. Societa Consortile Per Azioni | Fan or propeller, with shape memory |
| US20060140772A1 (en) * | 2004-12-24 | 2006-06-29 | Mcmillan Alison J | Composite blade |
| US20070110583A1 (en) * | 2005-09-24 | 2007-05-17 | Rolls-Royce Plc | Vane assembly |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103511083A (en) * | 2012-06-25 | 2014-01-15 | 通用电气公司 | Systems and methods to control flow in a rotor wheel |
| CN103511083B (en) * | 2012-06-25 | 2017-04-12 | 通用电气公司 | Systems and methods to control flow in a rotor wheel |
| CN107315403A (en) * | 2016-04-27 | 2017-11-03 | 通用电气公司 | With the performance model control machinery of calibration |
| CN107315403B (en) * | 2016-04-27 | 2021-04-09 | 通用电气公司 | Controlling a machine with a calibrated performance model |
| CN107725215A (en) * | 2016-08-11 | 2018-02-23 | 通用电气公司 | For the inlet guide vane component for the air stream swirl flow distortion for reducing aircraft aft-fan |
| CN107725215B (en) * | 2016-08-11 | 2022-04-19 | 通用电气公司 | Inlet guide vane assembly for reducing airflow swirl distortion of an aircraft aft fan |
| CN109458362A (en) * | 2017-09-06 | 2019-03-12 | 赛峰航空器发动机 | Reinforce the composite material casing of shape |
| US10995634B2 (en) | 2017-09-06 | 2021-05-04 | Safran Aircraft Engines | Composite material casing of stiffening shape |
| CN109458362B (en) * | 2017-09-06 | 2021-08-10 | 赛峰航空器发动机 | Reinforced shape composite material shell |
| CN110005640A (en) * | 2018-01-04 | 2019-07-12 | 中国航发商用航空发动机有限责任公司 | A kind of fan blade, compressor and aero-engine |
| CN110005641A (en) * | 2018-01-04 | 2019-07-12 | 中国航发商用航空发动机有限责任公司 | Compressor blade and compressor flow separation control method |
| CN110005640B (en) * | 2018-01-04 | 2020-07-03 | 中国航发商用航空发动机有限责任公司 | Fan blade, compressor and aircraft engine |
Also Published As
| Publication number | Publication date |
|---|---|
| US20120045318A1 (en) | 2012-02-23 |
| CH703659A2 (en) | 2012-02-29 |
| JP2012041929A (en) | 2012-03-01 |
| DE102011052597A1 (en) | 2012-04-26 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102400956A (en) | Method and apparatus for air flow control | |
| US8355854B2 (en) | Methods relating to gas turbine control and operation | |
| EP2589751B1 (en) | Turbine last stage flow path | |
| US5911679A (en) | Variable pitch rotor assembly for a gas turbine engine inlet | |
| US10077694B2 (en) | Power generation system exhaust cooling | |
| US20160305261A1 (en) | High pressure ratio twin spool industrial gas turbine engine with dual flow high spool compressor | |
| US20160215694A1 (en) | High pressure ratio twin spool industrial gas turbine engine | |
| US10273976B2 (en) | Actively morphable vane | |
| JP6216166B2 (en) | Airfoil | |
| US20170298826A1 (en) | Industrial gas turbine engine with turbine airfoil cooling | |
| EP3070295A1 (en) | Power generation system having compressor creating excess air flow | |
| CN107567533B (en) | Apparatus and method for retrofitting a combined cycle power plant | |
| US10060316B2 (en) | Power generation system exhaust cooling | |
| US10151211B2 (en) | Apparatus and process for converting an aero gas turbine engine into an industrial gas turbine engine for electric power production | |
| EP3070290A1 (en) | Power generation system having compressor creating excess air flow and turbo-expander to increase turbine exhaust gas mass flow | |
| EP3070299A1 (en) | Power generation system having compressor creating excess air flow and supplemental compressor therefor | |
| EP3070275A1 (en) | Power generation system having compressor creating excess air flow and heat exchanger therefor | |
| WO2015038768A1 (en) | High pressure ratio twin spool industrial gas turbine engine | |
| JP6749772B2 (en) | Power generation system with compressor for generating excess air flow and turbo expander for cooling inlet air | |
| EP3044430B1 (en) | Industrial gas turbine engine | |
| JP2011102584A (en) | Gas turbine compressor and method for operating the same | |
| JP4895465B2 (en) | Flame temperature control and adjustment system for single shaft gas turbine | |
| EP3070300A1 (en) | Power generation system having compressor creating excess air flow and cooling fluid injection therefor | |
| JP6291245B2 (en) | Supercharged combined cycle system with airflow bypass to HRSG and fan | |
| CN106164445A (en) | Variable limit value power for gas turbine controls |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20120404 |