CN109519225A - A kind of radial-inward-flow turbine device with damping and sealing structure - Google Patents
A kind of radial-inward-flow turbine device with damping and sealing structure Download PDFInfo
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- CN109519225A CN109519225A CN201811319811.2A CN201811319811A CN109519225A CN 109519225 A CN109519225 A CN 109519225A CN 201811319811 A CN201811319811 A CN 201811319811A CN 109519225 A CN109519225 A CN 109519225A
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- radial
- inward
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- impeller
- flow turbine
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- 238000007789 sealing Methods 0.000 title claims abstract description 21
- 238000013016 damping Methods 0.000 title claims abstract description 15
- 230000008676 import Effects 0.000 claims abstract description 13
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 5
- 230000004323 axial length Effects 0.000 claims description 2
- 230000015572 biosynthetic process Effects 0.000 claims description 2
- 230000004044 response Effects 0.000 abstract description 8
- 239000012530 fluid Substances 0.000 description 5
- 230000000694 effects Effects 0.000 description 4
- 239000007789 gas Substances 0.000 description 4
- 230000008901 benefit Effects 0.000 description 3
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 description 2
- 230000009471 action Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- 208000016285 Movement disease Diseases 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 229910002092 carbon dioxide Inorganic materials 0.000 description 1
- 239000001569 carbon dioxide Substances 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000004140 cleaning Methods 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 229910017052 cobalt Inorganic materials 0.000 description 1
- 239000010941 cobalt Substances 0.000 description 1
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 210000004907 gland Anatomy 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000003345 natural gas Substances 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 229910000601 superalloy Inorganic materials 0.000 description 1
- 230000001052 transient effect Effects 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/20—Specially-shaped blade tips to seal space between tips and stator
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/16—Form or construction for counteracting blade vibration
-
- 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
- F05D2240/55—Seals
- F05D2240/56—Brush seals
Abstract
A kind of radial-inward-flow turbine device with damping and sealing structure, when work, working medium is entered in radial-inward-flow turbine device by air inlet volute first, it subsequently enters in nozzle ring, the power pressure of high temperature and pressure is gradually reduced, flow velocity is gradually increased, the working medium of nozzle ring outlet enters from impeller inlet, the expansion work in impeller, pressure and temperature is gradually reduced, working medium first passes around the water conservancy diversion for the closed flow that vane inlet shroud and wheel hub are formed in impeller, it then reaches and continues expansion work in the middle part of radial-inward-flow turbine impeller blade, eventually pass through the closed flow that blade exit shroud and wheel hub are formed, the working medium of low-pressure low-temperature is discharged from radial-inward-flow turbine device by outlet flow.The present invention by using blade import and export shroud structure, cooperate the brush seal between wheel cap and impeller blade, while greatly improving rigidity, reducing vibratory response, guarantee safety in operation, the pneumatic efficiency of radial-inward-flow turbine device is improved, there is important engineering significance and wide application prospect.
Description
Technical field
The present invention relates to a kind of turbomachine devices, and in particular to a kind of centripetal with damping and sealing structure
Leveling device.
Background technique
Turbomachine is a kind of power-equipment based on continuous rotation blade, can be realized fluid working substance and axis power
Between energy conversion, including steam turbine, combustion gas turbine and turbocompressor etc., production level is that measure a country whole
One of most important mark of body industrial might.By Working fluid flow direction turbomachine can be divided into radial-flow type, diameter-axial-flow type and
Axial turbine, wherein Working fluid flow direction is referred to as radial-inward-flow turbine from the radial-flow type and diameter-axial turbine at outer circumferential center.Phase
Specific run off formula turbine, radial-inward-flow turbine have that size is small, light-weight, the service life is long, structure is simple, convenient operating maintenance, cheap
The advantages that.Especially for the lesser design conditions of flow, the efficiency of radial-inward-flow turbine is higher.It is increasingly developed with engineering technology,
Radial-inward-flow turbine is widely used in recent years, not only can be used in, the turbocharging of small-power gas-turbine installation and diesel engine
Device, but also as the turbo-expander in air separation plant and natural gas liquefaction device.
Shroud structure is usually used in high-power axial turbine, such as steam turbine, gas turbine, aero-engine, makees
With being to reduce blade vibration response, the vibrational energy for the blade that dissipated using the rubbing action between adjacent blades is subtracted to reach
The effect of vibration.Shroud structure is located at vane tip, in static state, there are primary clearance between the adjacent shroud of blade, when operation
Under the action of centrifugal force, blade twists recovery, so that adjacent blades shroud contact surface is mutually adjacent to, when blade vibration,
The vibrational energy of the Relative sliding effect dissipation blade of generation between shroud contact surface, reduces blade vibration stress, to improve
The service life of blade and the security reliability of operation.Brush seal is a kind of Efficient Damping sealing that developed recently gets up, leakage
Amount is 1st/10th to ten/5th of Comb Labyrinth Seals, and allows the serious decentraction of transient state between sound and keep sealing energy
Power is constant, has not only improved unit efficiency but also has improved the stability of rotor, is the key technology of modern advanced turbomachinery development
One of, it has been applied to the turbomachines such as aero-engine, industry gas turbine and steam turbine.
Radial-inward-flow turbine general size is smaller, and revolving speed is higher.Double shrouded wheel wheel cap is attached on blade, and quality is big, centrifugal force
Greatly, and there is difficult cleaning of drawback, it is difficult to operation is in the fluid working substance with impurity, and in half-opened impeller, wheel cap
Blade tip clearance between blade can then largely effect on the pneumatic efficiency of turbine.In order to improve efficiency, need to reduce to the greatest extent leaf top
Therefore gap is easily worn at the leaf top that the blade flutter that turbo wheel occurs in operation causes impeller to be imported and exported, right
The pneumatic efficiency of radial-inward-flow turbine, impeller life and safe operation are totally unfavorable.To sum up, current radial-inward-flow turbine device is needed into one
Step improves, and to reduce the vibratory response and leakage rate of radial-inward-flow turbine impeller blade, improves unit efficiency, ensures operational safety
Property.Therefore, there is a kind of radial-inward-flow turbine device with damping and sealing structure proposed by the present invention important engineering to anticipate
Justice.
Summary of the invention
In view of the above-mentioned deficiencies in the prior art, it is an object of the present invention to provide a kind of with damping and sealing structure
Radial-inward-flow turbine device is mainly used in the slow-speed of revolution, powerful radial-inward-flow turbine device, can reduce the vibration of radial-inward-flow turbine impeller blade
Dynamic response and leakage rate improve unit efficiency, ensure safety in operation, before important engineering significance and wide application
Scape.
The present invention adopts the following technical scheme that realize:
A kind of radial-inward-flow turbine device with damping and sealing structure, including spiral case, are arranged at spiral case center
Several nozzle rings in wheel hub circumferential direction and the radial-inward-flow turbine impeller blade at center and centripetal is arranged in wheel hub and wheel cap
The outlet flow of turbo wheel blade exit connection；Wherein,
Wheel hub and radial-inward-flow turbine impeller blade collectively constitute impeller, the inlet and outlet difference of radial-inward-flow turbine impeller blade
It is provided with vane inlet shroud and blade exit shroud, and in impeller channel, is adopted between wheel cap and radial-inward-flow turbine impeller blade
Use brush seal；
When work, working medium is entered in radial-inward-flow turbine device by air inlet volute first, is subsequently entered in nozzle ring, high temperature
The power pressure of high pressure is gradually reduced, and flow velocity is gradually increased, and the working medium of nozzle ring outlet enters from impeller inlet, swollen in impeller
Swollen acting, pressure and temperature are gradually reduced, and working medium first passes around the closing stream that vane inlet shroud and wheel hub are formed in impeller
The water conservancy diversion in road then reaches and continues expansion work in the middle part of radial-inward-flow turbine impeller blade, eventually passes through blade exit shroud and wheel hub
The working medium of the closed flow of formation, low-pressure low-temperature is discharged from radial-inward-flow turbine device by outlet flow.
A further improvement of the present invention lies in that several nozzle rings are arranged between spiral case internal diameter and impeller outer diameter, consistency is
The ratio of chord length and pitch is 1.5, and the gap between nozzle ring internal diameter and impeller outer diameter is 10mm；And spiral case internal diameter dv, nozzle
Ring outside diameter dnWith impeller outer diameter drGeometrical relationship be expressed as follows:
dv=dn=1.5dr。
A further improvement of the present invention lies in that vane inlet shroud and blade exit shroud are arranged in radial-inward-flow turbine impeller leaf
At the top of piece, vane inlet shroud arranges that blade exit shroud is concordant with blade exit runner since vane inlet runner, thick
Degree is high 20% of radial-inward-flow turbine impeller blade import leaf, and two shrouds circumferentially flow by whole circle arrangement, vane inlet shroud edge
To the length l in directioninWith blade radial length lr, blade exit shroud is along the length l for flowing to directionoutWith blade axial length
laGeometrical relationship be respectively as follows:
Compared with prior art, the present invention has following beneficial technical effect:
The present invention passes through the advantage for successfully integrating a variety of prior arts, has carried out reformed AHP for radial-inward-flow turbine device,
A kind of radial-inward-flow turbine device with damping and sealing structure is proposed, impeller rigidity can improved, reduce impeller leaf
The vibratory response of piece while ensureing safety in operation, improves leakage situation, improves pneumatic efficiency.Wherein, working medium first by into
Gas spiral case enters in radial-inward-flow turbine device, subsequently enters in nozzle ring, and wherein the power pressure of high temperature and pressure is gradually reduced, flow velocity
It is gradually increased.Nozzle ring outlet working medium from radial-inward-flow turbine impeller inlet enter, the expansion work in impeller, pressure and temperature by
Gradually decline.Working medium first passes around the water conservancy diversion for the closed flow that vane inlet shroud and wheel hub are formed in impeller, then reaches leaf
Continue expansion work in the middle part of piece, eventually pass through the closed flow that blade exit shroud and wheel hub are formed, the working medium of low-pressure low-temperature by
Outlet flow is discharged from radial-inward-flow turbine device.In impeller channel, brush seal is used between wheel cap and impeller blade.The present invention
Technical solution can simply implement radial-inward-flow turbine highly effective and safe operation.
Double shrouded wheel adheres to wheel cap on rotor leaf top, and quality is larger, therefore centrifugal force is big, and it is unfavorable to be safely operated to impeller.
Shroud structure is arranged in the import and export of radial-inward-flow turbine impeller blade in the present invention, the quality of impeller can be made smaller, therefore have
Smaller centrifugal force is conducive to the safe operation of high-speed rotating radial-inward-flow turbine impeller, is more suitable for high load working condition.For to
Heart turbine import and export blade situation easy to wear, vibratory response can be greatly reduced by adding shroud structure, increase rigidity, especially
Suitable for supercritical carbon dioxide etc. for working medium air-flow power is big, radial-inward-flow turbine that exciting force is big.Meanwhile blade import and export
Shroud structure can also play guide functions, movement disorder caused by preventing impeller inlet from having a common boundary because of moving-stator blade and makes impeller
Working fluid flow in outlet flow is more smoothly.
Wherein, the brush filament of brush seal mainly uses cobalt base superalloy, has low brittleness, high tenacity, can guarantee to transport
It does not fracture during row, and high performance welding procedure guarantees not falling off for brush filament, the bristle tuft thickness and height of optimization guarantee
The reasonable combination of obturaging property, brush filament material and coating material guarantees the operation that sealing is stable, safe.Gas between wheel cap and impeller
Envelope uses brush seal, and advantage is mainly reflected in good dynamic sealing performance, due to the brush filament and seal member of brush seal
There is certain tilt angle, efficiently avoids causing and sealing element because direct long-time high-frequency and seal member touch after mill
Between seal clearance permanently increase.
In conclusion the present invention uses the shroud structure of blade import and export, cooperate the brush between wheel cap and impeller blade
Formula sealing improves radial-inward-flow turbine device while greatly improving rigidity, reducing vibratory response, guarantee safety in operation
Pneumatic efficiency has important engineering significance and wide application prospect.
Detailed description of the invention
Fig. 1 is a kind of threedimensional model of the radial-inward-flow turbine device with damping and sealing structure of the present invention.
Fig. 2 is a kind of impeller meridional section figure of the radial-inward-flow turbine device with damping and sealing structure of the present invention.
In figure, 1- spiral case, 2- nozzle ring, 3- wheel hub, 4- radial-inward-flow turbine impeller blade, 5- vane inlet shroud, 6- blade
Export shroud, 7- wheel cap, 8- brush seal, 9- outlet flow.
Specific embodiment
The present invention will be further explained below with reference to the attached drawings.
Referring to FIG. 1 and FIG. 2, a kind of radial-inward-flow turbine device with damping and sealing structure provided by the invention, packet
Include spiral case 1, wheel hub 3 and wheel cap 7 at 1 center of spiral case be set, be arranged in several nozzle rings 2 in 3 circumferential direction of wheel hub and in
The outlet flow 9 of 4 outlet of radial-inward-flow turbine impeller blade 4 and radial-inward-flow turbine impeller blade at the heart；Wherein, centripetal
The inlet and outlet of flat impeller blade 4 is respectively arranged with vane inlet shroud 5 and blade exit shroud 6, and in impeller channel
In, brush seal 8 is used between wheel cap 7 and radial-inward-flow turbine impeller blade 4；Wherein, wheel hub 3 and radial-inward-flow turbine impeller blade 4 are total
With composition impeller.Working medium is entered in radial-inward-flow turbine device by spiral case 1 first, is subsequently entered in nozzle ring 2, wherein high temperature and pressure
Power pressure is gradually reduced, and flow velocity is gradually increased.The working medium that nozzle ring 2 exports enters from 3 import of radial-inward-flow turbine impeller, in wheel hub
Expansion work in 3 runners formed with radial-inward-flow turbine impeller blade 4, pressure and temperature are gradually reduced.During this, working medium is first
The water conservancy diversion for the closed flow that vane inlet shroud 5 and wheel hub 3 are formed is first passed through, middle part of blade is then reached and continues expansion work,
Eventually pass through the closed flow that blade exit shroud 6 and wheel hub 3 are formed, the working medium of low-pressure low-temperature is by outlet flow 9 from centripetal
It is discharged in leveling device.
Wherein, nozzle ring is arranged between spiral case internal diameter and impeller outer diameter, and the ratio of consistency, that is, chord length and pitch is 1.5,
Gap between nozzle ring internal diameter and impeller outer diameter is 10mm.Spiral case internal diameter dv, nozzle ring outside diameter dnWith impeller outer diameter drGeometry
Relationship is expressed as follows:
dv=dn=1.5dr
Wherein, vane inlet and outlet shroud are located at leaf top, and import shroud arranges that outlet is enclosed since vane inlet runner
Band is concordant with blade exit runner, and thickness is high 20% of impeller blade import leaf.Shroud circumferentially arrange by whole circle, import
Shroud is along the length l for flowing to directioninWith blade radial length lr, outlet shroud is along the length l for flowing to directionoutWith blade axial direction
Length laGeometrical relationship be respectively as follows:
lin=0.05lr
lout=0.05la
Double shrouded wheel quality is larger, therefore centrifugal force is big, and it is unfavorable to be safely operated to impeller.In radial-inward-flow turbine impeller blade
Shroud structure is arranged in import and export, and the quality of impeller can be made smaller, be more suitable for high load working condition.It is passed in and out for radial-inward-flow turbine
Blade situation easy to wear at mouthful, vibratory response can be greatly reduced by adding shroud structure, increase rigidity.Meanwhile blade passes in and out
Shroud structure at mouthful can also play guide functions.Sealing gland between wheel cap and impeller uses brush seal, can be into one
Step promotes pneumatic efficiency.Therefore, the present invention by using blade import and export shroud structure, cooperation wheel cap and impeller blade it
Between brush seal improve efficiency while guaranteeing safety in operation, have important engineering significance and wide application
Prospect.
Claims (3)
1. a kind of radial-inward-flow turbine device with damping and sealing structure, which is characterized in that including spiral case (1), setting exists
Wheel hub (3) and wheel cap (7) at spiral case (1) center, be arranged in wheel hub (3) circumferential direction several nozzle rings (2) and center at
Radial-inward-flow turbine impeller blade (4) and radial-inward-flow turbine impeller blade (4) outlet outlet flow (9)；Wherein,
Wheel hub (3) and radial-inward-flow turbine impeller blade (4) collectively constitute impeller, the inlet and outlet of radial-inward-flow turbine impeller blade (4)
Place is respectively arranged with vane inlet shroud (5) and blade exit shroud (6), and in impeller channel, wheel cap (7) and radial-inward-flow turbine
Brush seal (8) are used between impeller blade (4)；
When work, working medium is entered in radial-inward-flow turbine device by air inlet volute (1) first, is subsequently entered in nozzle ring (2), wherein high
The power pressure of warm high pressure is gradually reduced, and flow velocity is gradually increased, and the working medium of nozzle ring (2) outlet enters from impeller inlet, in leaf
Expansion work in wheel, pressure and temperature are gradually reduced, and working medium first passes around vane inlet shroud (5) and wheel hub (3) in impeller
The water conservancy diversion of the closed flow of formation then reaches and continues expansion work in the middle part of radial-inward-flow turbine impeller blade (4), eventually passes through blade
Export the closed flow that shroud (6) and wheel hub (3) are formed, the working medium of low-pressure low-temperature is by outlet flow (9) from radial-inward-flow turbine device
Middle discharge.
2. a kind of radial-inward-flow turbine device with damping and sealing structure according to claim 1, which is characterized in that
Several nozzle rings (2) are arranged between spiral case internal diameter and impeller outer diameter, and the ratio of consistency, that is, chord length and pitch is 1.5, nozzle ring
Gap between internal diameter and impeller outer diameter is 10mm；And spiral case internal diameter dv, nozzle ring outside diameter dnWith impeller outer diameter drGeometrical relationship
It is expressed as follows:
dv=dn=1.5dr。
3. a kind of radial-inward-flow turbine device with damping and sealing structure according to claim 1, which is characterized in that
Vane inlet shroud (5) and blade exit shroud (6) setting are at the top of radial-inward-flow turbine impeller blade (4), vane inlet shroud (5)
It is arranged since vane inlet runner, blade exit shroud (6) is concordant with blade exit runner, and thickness is radial-inward-flow turbine leaf
Impeller blade (4) import leaf it is high 20%, two shrouds circumferentially whole circle arrangement, vane inlet shroud (5) is along the length for flowing to direction
Spend linWith blade radial length lr, blade exit shroud (6) is along the length l for flowing to directionoutWith blade axial length laGeometry
Relationship is respectively as follows:
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811319811.2A CN109519225B (en) | 2018-11-07 | 2018-11-07 | Centripetal turbine device with vibration damping and sealing structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811319811.2A CN109519225B (en) | 2018-11-07 | 2018-11-07 | Centripetal turbine device with vibration damping and sealing structure |
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| Publication Number | Publication Date |
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| CN109519225A true CN109519225A (en) | 2019-03-26 |
| CN109519225B CN109519225B (en) | 2020-03-17 |
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| CN201811319811.2A Active CN109519225B (en) | 2018-11-07 | 2018-11-07 | Centripetal turbine device with vibration damping and sealing structure |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110469369A (en) * | 2019-08-20 | 2019-11-19 | 中国船舶重工集团公司第七一九研究所 | A kind of kW grade supercritical carbon dioxide radial turbine structure with splitterr vanes |
| CN114542198A (en) * | 2022-03-11 | 2022-05-27 | 天津大学 | Turbine expansion power generation all-in-one machine |
| EP4269752A1 (en) * | 2022-04-28 | 2023-11-01 | Hamilton Sundstrand Corporation | Additively manufactured multi-metallic adaptive rotor tip seals |
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| JP2007309139A (en) * | 2006-05-16 | 2007-11-29 | Toyota Motor Corp | Turbocharger |
| CN107355271A (en) * | 2017-07-25 | 2017-11-17 | 航天推进技术研究院 | A kind of organic Rankine bottoming cycle multikilowatt TRT |
| GB2502868B (en) * | 2012-04-05 | 2018-06-27 | Snecma | A compressor guide-vane stage for a turbine engine |
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| CN1186540A (en) * | 1995-12-07 | 1998-07-01 | 株式会社荏原制作所 | Turbine machine and manufacture thereof |
| JP2007309139A (en) * | 2006-05-16 | 2007-11-29 | Toyota Motor Corp | Turbocharger |
| GB2502868B (en) * | 2012-04-05 | 2018-06-27 | Snecma | A compressor guide-vane stage for a turbine engine |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110469369A (en) * | 2019-08-20 | 2019-11-19 | 中国船舶重工集团公司第七一九研究所 | A kind of kW grade supercritical carbon dioxide radial turbine structure with splitterr vanes |
| CN114542198A (en) * | 2022-03-11 | 2022-05-27 | 天津大学 | Turbine expansion power generation all-in-one machine |
| EP4269752A1 (en) * | 2022-04-28 | 2023-11-01 | Hamilton Sundstrand Corporation | Additively manufactured multi-metallic adaptive rotor tip seals |
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|---|---|
| CN109519225B (en) | 2020-03-17 |
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