CN111425259A - Magnetic suspension supersonic speed turbo expander - Google Patents
Magnetic suspension supersonic speed turbo expander Download PDFInfo
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- CN111425259A CN111425259A CN202010123935.4A CN202010123935A CN111425259A CN 111425259 A CN111425259 A CN 111425259A CN 202010123935 A CN202010123935 A CN 202010123935A CN 111425259 A CN111425259 A CN 111425259A
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- 239000000725 suspension Substances 0.000 title claims abstract description 18
- 230000007704 transition Effects 0.000 claims description 33
- 238000005339 levitation Methods 0.000 claims description 10
- 239000012530 fluid Substances 0.000 claims description 8
- 230000008859 change Effects 0.000 claims description 6
- 238000006243 chemical reaction Methods 0.000 claims description 5
- 238000010248 power generation Methods 0.000 claims description 3
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 238000005461 lubrication Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
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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
- F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
- F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
- F01D1/04—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines traversed by the working-fluid substantially axially
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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
- F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
- F01D15/10—Adaptations for driving, or combinations with, electric generators
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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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
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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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
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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
- 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
- F01D5/141—Shape, i.e. outer, aerodynamic form
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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
- 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
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
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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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C32/00—Bearings not otherwise provided for
- F16C32/04—Bearings not otherwise provided for using magnetic or electric supporting means
- F16C32/0402—Bearings not otherwise provided for using magnetic or electric supporting means combined with other supporting means, e.g. hybrid bearings with both magnetic and fluid supporting means
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Architecture (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a magnetic suspension supersonic speed turboexpander, which sequentially comprises the following components in the direction of gas inlet and outlet: the device comprises an air inlet, a rectifying grid, a nozzle, an impeller, a generator and an air outlet; the nozzle adopts a supersonic nozzle, subsonic air enters the throat part of the nozzle through a convergent section to reach sonic speed, and then enters the nozzle outlet through a divergent section to reach supersonic speed; the radial bearing and the thrust bearing in the generator cavity are both magnetic suspension bearings; the impeller adopts an axial flow impeller, and two concentric flow channels are adopted between every two blades. The turboexpander has the characteristics of small volume, high energy density, low loss and no oil.
Description
Technical Field
The invention relates to the technical field of expanders, in particular to a magnetic suspension supersonic speed turboexpander.
Background
A turboexpander is a prime mover for realizing energy conversion by high-pressure gas expansion, and is mainly characterized in that gas with certain pressure is subjected to adiabatic expansion in the turboexpander to do work externally to consume internal energy of the gas, so that the gas can be cooled while the energy is output.
Disclosure of Invention
In order to overcome the defects in the prior art, the invention provides a magnetic suspension supersonic speed turboexpander which has the characteristics of small volume, large energy density, low loss and no oil.
In order to achieve the purpose, the invention adopts the following technical scheme that:
a magnetic suspension supersonic speed turboexpander comprises the following components in sequence according to the gas inlet and outlet directions: the device comprises an air inlet, a rectifying grid, a nozzle, an impeller, a generator and an air outlet;
the nozzle adopts a supersonic nozzle, and sequentially comprises the following components in the direction of gas inlet and outlet: the nozzle comprises a nozzle inlet, a convergence section, a nozzle throat, a diffusion section and a nozzle outlet;
the convergent section and the nozzle throat part are matched for changing gas from subsonic speed to sonic speed, and the convergent section and the nozzle throat part are in smooth transition; the nozzle throat and the diffuser section cooperate to change the gas from sonic to supersonic, the diffuser section and the nozzle throat having a smooth transition therebetween;
the cavity of the generator comprises: a generator shaft;
the impeller is arranged on the end part of the rotating shaft of the generator, which faces to one side of the nozzle;
the supersonic gas at the outlet of the nozzle enters the impeller and is used for driving the impeller to rotate, and the impeller is used for synchronously driving the rotating shaft of the generator to rotate so as to realize the power generation of the generator;
the gas passes through the expander casing to the gas outlet after coming out of the impeller.
Still include in the cavity of generator: radial bearings, thrust bearings; the radial bearing is used for suspending the rotating shaft of the generator; the thrust bearing is used for limiting the axial movement of the rotating shaft of the generator during rotation.
The radial bearing and the thrust bearing both adopt magnetic suspension bearings; the magnetic suspension bearing detects a shaft deviation signal of the rotating shaft of the generator through the position sensor and sends the shaft deviation signal to the controller, and the controller controls the current in the electromagnet through the power amplifier so as to control the magnitude of the electromagnetic force and enable the rotating shaft of the generator to suspend at a specified position.
The impeller adopts an axial flow impeller; and an arc-shaped flow channel is formed between any two adjacent blades on the impeller.
The upper surface of each blade is a crescent cambered surface, and the line type of the front edge part a of each blade is divided into the following parts in sequence: an inlet straight line EF, an inlet upper transition arc FG, a concentric upper arc GH, an outlet upper transition arc HI and an outlet straight line IJ; the line shape of the trailing edge portion b of each blade is divided into the following parts in order: an inlet lower transition arc AB, a concentric lower arc BC, and an outlet lower transition arc CD;
the concentric upper circular arc GH of the front edge portion a and the concentric lower circular arc BC of the rear edge portion b are concentric circular arcs and are symmetrical along the central axis of the blade, and the concentric angle number of the concentric lower circular arc BC is larger than that of the concentric upper circular arc GH.
Between any two adjacent vanes X, Y, an inter-concentric flow path is formed between the concentric upper arc GH at the front edge portion a of the vane Y and the concentric lower arc BC at the rear edge portion b of the vane X.
The supersonic fluid flows in the concentric flow channel between two adjacent vanes X, Y in the following way: the inlet upper transition arc FG of the front edge part a of the blade Y and the inlet lower transition arc AB of the rear edge part b of the blade X gradually change the intake supersonic uniform airflow to the vortex flow, the concentric upper arc GH of the front edge part a of the blade Y and the concentric lower arc BC of the rear edge part b of the blade X keep the vortex flow, and the outlet upper transition arc HI of the front edge part a of the blade Y and the outlet lower transition arc CD of the rear edge part b of the blade X convert the vortex flow back to the blade outlet uniform airflow.
The degree of reaction of the turboexpander was 0.25.
In the diffuser section, E1F1 is a central line, A1C1 is a transition arc, B1D1 and A1C1 are axisymmetric with respect to E1F1, C1G1 is a straight line, and C1G1 is tangent to A1C 1.
The nozzle outlet angle α is the angle between the centerline E1F1 and a horizontal line perpendicular to the nozzle air intake direction, the nozzle outlet angle α being set at 16.
The invention has the advantages that:
(1) the greater the speed at which the turboexpander enters the impeller, the greater the work output. The turboexpander has the design reaction degree of 0.25, adopts the supersonic nozzle, and has an outlet Mach number of more than 1.7, so that the supersonic speed can be realized in the nozzle.
(2) The turboexpander is supported by the magnetic suspension bearing, and the magnetic suspension bearing is used as a non-contact bearing and can bear high rotating speed, and the rotating speed is higher, and the volume is smaller. The magnetic suspension bearing structure cancels a reduction box part, and the generator adopts a permanent magnet generator, so that the energy density is high, the volume is small, and the whole volume of the turboexpander is very small. The magnetic suspension bearing is used as a non-contact bearing, oil lubrication is not needed, oil is completely not contained in the expansion machine, oil pollution is avoided, and the turbo expansion machine can be used in industries with strict requirements on oil pollution.
(3) The rotating shaft of the generator of the turboexpander is in a suspension state, and no friction loss exists, so that compared with a common expander, the turboexpander has the advantages of lower mechanical loss and higher efficiency.
(4) The impeller of the turboexpander adopts the large-angle flow channel between two concentric circles, so that supersonic fluid can flow through the impeller without causing local impact.
(5) The expander uses the generator as an energy output component, finally generates electric energy which can be widely applied to various industries, so that the expander is suitable for multiple occasions.
(6) The impeller adopts an axial flow impeller, two concentric flow channels are adopted between every two blades, and the two concentric flow channels can realize the flowing of supersonic fluid without causing local impact.
(7) The supersonic fluid flows in the blade flow channel in the following flowing mode: the inlet transition arc gradually changes the uniform flow of the inlet supersonic speed to the vortex flow, the concentric circular arc part maintains the vortex flow, the outlet transition arc converts the vortex flow to return to the outlet of the blade for uniform airflow, the supersonic speed fluid can flow through, and the local impact cannot be caused.
Drawings
FIG. 1 is a schematic diagram of a magnetic levitation supersonic turboexpander according to the present invention.
FIG. 2 is a schematic view of a supersonic nozzle.
FIG. 3 is a schematic structural view of the supersonic nozzle.
Fig. 4 is a schematic view of a magnetic bearing.
Fig. 5 is a schematic structural view of the impeller.
FIG. 6 is a schematic view of the flow path between two adjacent blades viewed from the Z direction.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
As shown in fig. 1, a magnetic levitation supersonic turboexpander comprises, in order from the inlet to the outlet of gas: the device comprises an air inlet 1, a rectifying grid 2, a nozzle 3, an impeller 4, a generator 5 and an air outlet 6.
The gas enters a rectification grid 2 in the shell of the expansion machine from a gas inlet 1, and after the rectification grid 2 rectifies the gas to ensure the stability of the gas, the gas enters a nozzle 3.
The turbine expander has the design reaction degree of 0.25, so the nozzle 3 adopts a supersonic nozzle, the Mach number of the outlet of the nozzle 3 reaches more than 1.7, and supersonic speed can be realized in the nozzle 3.
As shown in fig. 2, the nozzle 3 includes, in order from the gas inlet to the gas outlet: a nozzle inlet 31, a convergent section 32, a nozzle throat 33, a divergent section 34, a nozzle outlet 35; the nozzle inlet 31 is subsonic, gas firstly enters the nozzle throat 33 through the convergent section 32 to reach sonic speed, and then enters the nozzle outlet 35 through the divergent section 34 to reach supersonic speed; finally, the supersonic gas at nozzle outlet 35 enters impeller 4.
When the nozzle is designed, the size of the throat part of the nozzle is the most critical, the enthalpy difference of the inlet and the outlet of the nozzle is obtained according to the pressure and the temperature of the inlet of the nozzle and the pressure and the temperature of the outlet of the nozzle to be achieved through isentropic expansion calculation, the isentropic expansion calculation refers to the prior art, the cross section area of the throat part of the nozzle, the height of the nozzle and the like are further obtained through calculation, and therefore the size of the throat part of the nozzle is obtained.
In the diffuser section 34, E1F1 is a center line, A1C1 is a transition arc, B1D1 and A1C1 are axisymmetric with respect to E1F1, and C1G1 is a straight line and tangent to A1C1, meanwhile, an angle α of the nozzle outlet and a chord length B1 of the nozzle are set, an angle α of the nozzle outlet is an included angle between the center line E1F1 and a horizontal line, the horizontal line is perpendicular to the air inlet direction of the nozzle 3, and an angle α of the nozzle outlet is generally set to about 16 °, so that the profile design of the diffuser section 34 can be completed.
The profile of the convergent section 32 can be obtained according to the profile design method of the divergent section 34, or the profile of the convergent section 32 can be defined by itself, only by ensuring that the convergent section 32 can smoothly transit with the nozzle throat 33. After the design of a single nozzle is finished, a central shaft is taken as an axis according to the circumferential array of the number of the nozzles, the number of the nozzles on the whole nozzle ring surface can be determined according to the designed molded lines of the convergent section 32 and the divergent section 34, then the circumferential array is carried out around the axis, and a plurality of nozzles are uniformly distributed on the nozzle ring surface, so that the whole nozzle ring can be formed.
The generator 5 comprises, in the cavity: generator shaft 51, radial bearing 52, thrust bearing 53.
The impeller 3 is mounted on one end of the generator shaft 51, specifically the end facing the nozzle side.
After supersonic gas at the nozzle outlet 35 enters the impeller 4, the impeller 4 is driven to rotate, and the impeller 4 synchronously drives the generator rotating shaft 51 to rotate, so that power generation of the generator 5 is realized.
The gas passes from the impeller 4 through the expander casing to the outlet 6.
The radial bearing 52 and the thrust bearing 53 both adopt magnetic suspension bearings, and the radial bearing 52 suspends the generator rotating shaft 51 by utilizing electromagnetic force; the thrust bearing 53 limits axial play of the generator shaft 51 when rotating by means of electromagnetic force.
As shown in fig. 4, the magnetic suspension bearing detects a shaft deviation signal of the generator rotating shaft 51 through a position sensor, and sends the shaft deviation signal to a controller, and the controller controls the current in the electromagnet through a power amplifier, thereby controlling the magnitude of the electromagnetic force, so that the generator rotating shaft 51 is suspended at a predetermined position.
As shown in fig. 5, the impeller 4 is an axial-flow impeller, which is an impeller in which gas flows in an axial direction when the turbo-expander is in operation; and the impeller 4 is an arc-shaped impeller, that is, an arc-shaped flow channel is formed between any two adjacent blades on the impeller 4.
FIG. 6 is a schematic view of the flow path between two adjacent blades viewed from the Z direction.
As shown in fig. 6, the upper surface of each blade is a crescent arc surface. As can be seen from fig. 6, the line type of the leading edge portion a of each blade is divided into the following parts in turn: an inlet straight line EF, an inlet upper transition arc FG, a concentric upper arc GH, an outlet upper transition arc HI and an outlet straight line IJ; the line shape of the trailing edge part b of each blade is divided into the following parts in turn: an inlet lower transition arc AB, a concentric lower arc BC, and an outlet lower transition arc CD. The concentric upper arcs GH of the front edge portion a and the concentric lower arcs BC of the rear edge portion b are concentric arcs and are symmetrical along the central axis of the blade, the number of concentric angles of the concentric lower arcs BC is larger than that of the concentric upper arcs GHC, the radius of the concentric upper arcs GH of the front edge portion a is R, and the radius of the concentric lower arcs BC of the rear edge portion b is R.
As shown in fig. 6, between any two adjacent vanes X, Y, an inter-concentric flow passage is formed between an upper concentric arc GH at the front edge a of the vane Y and a lower concentric arc BC at the rear edge b of the vane X.
The supersonic fluid flows in the concentric flow channel between two adjacent vanes X, Y in the following way: an inlet upper transition arc FG of a front edge part a of the blade Y and an inlet lower transition arc AB of a rear edge part b of the blade X gradually change the intake supersonic speed to flow uniformly to a vortex flow, a concentric upper arc GH of the front edge part a of the blade Y and a concentric lower arc BC of the rear edge part b of the blade X maintain the vortex flow, and an outlet upper transition arc HI of the front edge part a of the blade Y and an outlet lower transition arc CD of the rear edge part b of the blade X convert the vortex flow to return to a blade outlet uniform airflow; thereby enabling supersonic fluid flow therethrough without causing local impingement.
The invention is not to be considered as limited to the specific embodiments shown and described, but is to be understood to cover all modifications, equivalents, and alternatives falling within the spirit and scope of the invention as defined by the appended claims.
Claims (9)
1. A magnetic suspension supersonic speed turboexpander is characterized by comprising the following components in sequence according to the gas inlet-outlet direction: the device comprises an air inlet (1), a rectifier grid (2), a nozzle (3), an impeller (4), a generator (5) and an air outlet (6);
the nozzle (3) adopts a supersonic nozzle and sequentially comprises the following components in the direction of gas inlet and outlet: a nozzle inlet (31), a convergent section (32), a nozzle throat (33), a divergent section (34), a nozzle outlet (35);
the convergent section (32) and the nozzle throat (33) cooperate to change the gas from subsonic to sonic, the convergent section (32) and the nozzle throat (33) having a smooth transition therebetween; the nozzle throat (33) and the diffuser section (34) cooperate to change the gas from sonic to supersonic, the diffuser section (34) and the nozzle throat (33) having a smooth transition therebetween;
the generator (5) comprises, in the cavity: a generator shaft (51);
the impeller (4) is arranged on the end part of the generator rotating shaft (51) facing to one side of the nozzle;
the supersonic gas at the nozzle outlet (35) enters the impeller (4) and is used for driving the impeller (4) to rotate, and the impeller (4) is used for synchronously driving the rotating shaft (51) of the generator to rotate so as to realize the power generation of the generator (5);
the gas passes through the shell of the expansion machine to the gas outlet (6) after coming out of the impeller (4).
2. A magnetic levitation supersonic turbo expander according to claim 1, further comprising in the cavity of the generator (5): a radial bearing (52) and a thrust bearing (53); the radial bearing (52) is used for suspending the generator rotating shaft (51); the thrust bearing (53) is used for limiting the axial movement of the rotating shaft (51) of the generator during rotation.
3. A magnetic levitation supersonic turbo expander according to claim 2, wherein said radial bearing (52) and said thrust bearing (53) are magnetic levitation bearings; the magnetic suspension bearing detects a shaft deviation signal of the generator rotating shaft (51) through a position sensor and sends the shaft deviation signal to a controller, and the controller controls the current in the electromagnet through a power amplifier so as to control the magnitude of electromagnetic force and enable the generator rotating shaft (51) to suspend at a specified position.
4. A magnetic levitation supersonic turbo-expander according to claim 1, wherein the impeller (4) is an axial flow impeller; and an arc-shaped flow channel is formed between any two adjacent blades on the impeller (4).
5. The magnetic levitation supersonic turbo expander according to claim 4, wherein the upper surface of each blade is a crescent-shaped arc, and the front edge portion a of each blade is divided into the following sections in sequence: an inlet straight line EF, an inlet upper transition arc FG, a concentric upper arc GH, an outlet upper transition arc HI and an outlet straight line IJ; the line shape of the trailing edge portion b of each blade is divided into the following parts in order: an inlet lower transition arc AB, a concentric lower arc BC, and an outlet lower transition arc CD;
the concentric upper circular arc GH of the front edge portion a and the concentric lower circular arc BC of the rear edge portion b are concentric circular arcs and are symmetrical along the central axis of the blade, and the concentric angle number of the concentric lower circular arc BC is larger than that of the concentric upper circular arc GH.
6. The magnetic levitation supersonic turbo expander as claimed in claim 5, wherein a flow passage between concentric circles is formed between any two adjacent vanes X, Y, between the concentric upper arc GH of the leading edge portion a of the vane Y and the concentric lower arc BC of the trailing edge portion b of the vane X;
the supersonic fluid flows in the concentric flow channel between two adjacent vanes X, Y in the following way: the inlet upper transition arc FG of the front edge part a of the blade Y and the inlet lower transition arc AB of the rear edge part b of the blade X gradually change the intake supersonic uniform airflow to the vortex flow, the concentric upper arc GH of the front edge part a of the blade Y and the concentric lower arc BC of the rear edge part b of the blade X keep the vortex flow, and the outlet upper transition arc HI of the front edge part a of the blade Y and the outlet lower transition arc CD of the rear edge part b of the blade X convert the vortex flow back to the blade outlet uniform airflow.
7. A magnetically levitated supersonic turboexpander according to claim 1, wherein the degree of reaction of the turboexpander is 0.25.
8. The magnetic levitation supersonic turboexpander according to claim 1, wherein in the diffuser section (34), the section E1F1 is a center line, the section A1C1 is a transition arc, the section B1D1 and the section A1C1 are axisymmetric with respect to the section E1F1, the section C1G1 is a straight line, and the section C1G1 is tangential to the section A1C 1.
9. A magnetic levitation supersonic turbo expander according to claim 8, wherein the angle α of the nozzle outlet (35) is the angle between the centre line E1F1 and a horizontal line perpendicular to the inlet direction of the nozzle (3), the angle α of the nozzle outlet (35) being set to 16 °.
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| CN202010123935.4A CN111425259A (en) | 2020-02-27 | 2020-02-27 | Magnetic suspension supersonic speed turbo expander |
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| CN202010123935.4A CN111425259A (en) | 2020-02-27 | 2020-02-27 | Magnetic suspension supersonic speed turbo expander |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113914942A (en) * | 2021-08-19 | 2022-01-11 | 合肥通用机械研究院有限公司 | ORC device adopting supersonic speed turboexpander |
| CN116011126A (en) * | 2023-03-24 | 2023-04-25 | 蓝箭航天空间科技股份有限公司 | Design method of supersonic turbine nozzle and supersonic turbine nozzle |
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| US20030072649A1 (en) * | 2001-10-05 | 2003-04-17 | Kuhne Craig Miller | Reduced shock transonic airfoil |
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| CN102852560A (en) * | 2011-06-29 | 2013-01-02 | 株式会社日立制作所 | Supersonic turbine moving blade and axial-flow turbine |
| CN105909388A (en) * | 2015-02-20 | 2016-08-31 | 波音公司 | Flow Inlet For Supersonic Aircraft With Elliptical Compression Ramp |
| CN110439634A (en) * | 2019-08-19 | 2019-11-12 | 哈尔滨电气股份有限公司 | One kind being used for direct connection natural gas radial-inflow turboexpaner generating equipment |
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| CN116011126A (en) * | 2023-03-24 | 2023-04-25 | 蓝箭航天空间科技股份有限公司 | Design method of supersonic turbine nozzle and supersonic turbine nozzle |
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