CN112832871A - Nozzle and low-temperature turbo expander - Google Patents
Nozzle and low-temperature turbo expander Download PDFInfo
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- CN112832871A CN112832871A CN201911156194.3A CN201911156194A CN112832871A CN 112832871 A CN112832871 A CN 112832871A CN 201911156194 A CN201911156194 A CN 201911156194A CN 112832871 A CN112832871 A CN 112832871A
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- section
- nozzle
- inlet
- channel
- main body
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- 239000012530 fluid Substances 0.000 claims 2
- 239000000126 substance Substances 0.000 claims 1
- 239000007921 spray Substances 0.000 abstract description 3
- 239000007789 gas Substances 0.000 description 24
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 6
- 238000000926 separation method Methods 0.000 description 5
- 239000001307 helium Substances 0.000 description 4
- 229910052734 helium Inorganic materials 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 238000005057 refrigeration Methods 0.000 description 4
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 description 3
- 239000003345 natural gas Substances 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 2
- ATUOYWHBWRKTHZ-UHFFFAOYSA-N Propane Chemical compound CCC ATUOYWHBWRKTHZ-UHFFFAOYSA-N 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000011084 recovery Methods 0.000 description 2
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 1
- 238000004378 air conditioning Methods 0.000 description 1
- 239000012298 atmosphere Substances 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 239000010406 cathode material Substances 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000004927 fusion Effects 0.000 description 1
- 229930195733 hydrocarbon Natural products 0.000 description 1
- 150000002430 hydrocarbons Chemical class 0.000 description 1
- 239000001257 hydrogen Substances 0.000 description 1
- 229910052739 hydrogen Inorganic materials 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
- 239000007791 liquid phase Substances 0.000 description 1
- 229910052757 nitrogen Inorganic materials 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 238000005191 phase separation Methods 0.000 description 1
- 239000001294 propane Substances 0.000 description 1
- 239000002994 raw material Substances 0.000 description 1
- 238000011946 reduction process Methods 0.000 description 1
- 238000003860 storage Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 239000002912 waste gas Substances 0.000 description 1
Images
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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/047—Nozzle boxes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/045—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector for radial flow machines or engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/048—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector for radial admission
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Nozzles (AREA)
Abstract
The nozzle provided by the invention comprises an inlet section, a main body section and an outlet section, wherein a gas working medium is introduced into the main body section through the inlet section, then expands in the main body section and flows out through the outlet section, wherein: the gas working medium is transited from the inlet section of the channel with the rectangular cross section to the main body section of the conical channel in the flow channel, the nozzle provided by the invention replaces the original blade-shaped nozzle with the spray pipe of the conical channel, and simultaneously combines the advantages of the linear arc blade-shaped nozzle, the linear arc blade-shaped is adopted at the inlet and the gas working medium is transited into the conical channel. Compared with the rectangular section channel of the original blade profile, the conical channel has small on-way loss coefficient and energy loss under the conditions of same section area, same channel length and same flow, and can effectively improve the speed coefficient of the nozzle, so that the isentropic efficiency of the turboexpander is improved. In addition, the invention also provides a low-temperature turboexpander comprising the nozzle.
Description
Technical Field
The invention relates to the technical field of low-temperature liquefaction devices, in particular to a nozzle and a low-temperature turboexpander.
Background
Nature provides a large amount of gaseous raw materials for production and life, such as oxygen and nitrogen in the atmosphere, natural gas and helium in the subsurface, and the consumption and utilization amount of the gaseous energy is an important index of the scientific and technological progress of society. In order to effectively utilize these gas resources, it is necessary to treat and store these gases. Due to the low density of gases, liquefaction of the gas is essential for the transportation and storage of the gas. Adiabatic isentropic expansion is an important means for obtaining low temperature, and a turbo expander is an effective machine for realizing a process close to the adiabatic isentropic expansion, and plays an important role in some large-scale low-temperature systems, such as air liquefaction separation equipment and cryogenic hydrogen and helium liquefaction device systems.
The turboexpander is an effective machine for realizing a near adiabatic isentropic expansion process and is quite widely applied. In addition to being widely used in the field of gas separation and liquefaction, the liquid-phase separation device plays a vital role in various other fields. For example, in the refrigeration field, turboexpanders are used in air conditioning systems for aircraft. In the petrochemical field, turboexpanders are used for the separation of propane and heavier hydrocarbons in natural gas. The turboexpander can also be applied to the fields of natural gas energy recovery, organic Rankine cycle of low-temperature process devices, waste gas energy recovery of papermaking or other industries, impurity removal of mixed gas and the like.
With the rapid development of the advanced fields of nuclear fusion, high-energy physics, superconducting application, universe exploration and the like, large-scale low-temperature refrigeration equipment, particularly refrigeration equipment in a hydrogen-helium temperature region, is widely applied and becomes an indispensable basic supporting facility, and a low-temperature helium turbo expander is a key component of the whole low-temperature refrigeration system.
In the turbo expander, a gas working medium is subjected to an expansion and temperature reduction process at a through-flow part, the working medium enters a volute from a pipeline, airflow is uniformly distributed to a nozzle, first expansion is carried out in the nozzle, a part of specific enthalpy drop is converted into kinetic energy of the airflow, the pressure of the airflow is reduced, the temperature is reduced, the speed is increased, and then a working wheel is pushed to output external work. The air flow continues to expand in the working wheel, the specific enthalpy drop is further reduced, the air flow is converted into external work to be output, the pressure and the temperature continue to be reduced, and the air flow speed is reduced due to the fact that the working wheel outputs the external work, so that the nozzle is a key part for completing energy conversion in the turbo expander.
The existing nozzle types comprise two types, namely a blade-shaped nozzle and an axisymmetric nozzle. The blade-shaped nozzle generally comprises two similar blades and an upper end surface and a lower end surface which form a channel; an axisymmetric nozzle, also known as a nozzle, consists of a conical channel.
Because the size of the turboexpander applied to the low-temperature technical field is small, and the nozzle with parallel meridian planes and linear arc blade profiles is generally adopted in the low-temperature field due to the convenience in manufacturing, the nozzle has a rectangular section, the flow loss of the blade profiles is large, the velocity coefficient is low, and the flow channel efficiency is low.
Disclosure of Invention
In view of the above, there is a need to provide a nozzle and a low temperature turboexpander, which can effectively increase the velocity coefficient of the nozzle and increase the isentropic efficiency of the turboexpander, in view of the drawbacks of the prior art.
In order to achieve the purpose, the invention adopts the following technical scheme:
in one aspect, the present invention provides a nozzle comprising: an inlet section, a main body section and an outlet section, a gas working medium being introduced into said main body section through said inlet section, being expanded in said main body section and then flowing out through said outlet section, wherein: the gas working medium is transferred to the main body section of the conical channel at the inlet section with the rectangular section.
In some preferred embodiments, the inlet of the nozzle is a straight circular arc blade shape, and the gas working medium enters the inlet section through the inlet.
In some preferred embodiments, the conical passage has a cone angle a of 9-13 degrees.
In another aspect, the present invention further provides a low temperature turboexpander, comprising a nozzle, the nozzle comprising an inlet section, a main section and an outlet section, a gas working medium being introduced into the main section through the inlet section, expanded in the main section and then discharged through the outlet section, wherein: the gas working medium is transited from the inlet section of the channel with the rectangular cross section to the main body section of the conical channel in the flow channel.
In some preferred embodiments, the inlet of the nozzle is a straight circular arc blade shape, and the gas working medium enters the inlet section through the inlet.
In some preferred embodiments, the conical passage has a cone angle a of 9-13 degrees.
The invention adopts the technical scheme that the method has the advantages that:
the nozzle provided by the invention comprises an inlet section, a main body section and an outlet section, wherein a gas working medium is introduced into the main body section through the inlet section, then expands in the main body section and flows out through the outlet section, wherein: the gas working medium is transited from the inlet section of the channel with the rectangular cross section to the main body section of the conical channel in the flow channel, the nozzle provided by the invention replaces the original blade-shaped nozzle with the spray pipe of the conical channel, and simultaneously combines the advantages of the linear arc blade-shaped nozzle, the linear arc blade-shaped is adopted at the inlet and the gas working medium is transited into the conical channel. Compared with the rectangular section channel of the original blade profile, the conical channel has small on-way loss coefficient and energy loss under the conditions of same section area, same channel length and same flow, and can effectively improve the speed coefficient of the nozzle, so that the isentropic efficiency of the turboexpander is improved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is an isometric view of a nozzle provided by an embodiment of the present invention;
FIG. 2 is a front view of a nozzle provided in accordance with an embodiment of the present invention;
FIG. 3 provides a cross-sectional view of the nozzle of the embodiment of FIG. 2.
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.
Referring to fig. 1, 2 and 3, the present invention provides a nozzle, including: an inlet section 1, a main body section 2 and an outlet section 3, wherein a gas working medium is introduced into the main body section 2 through the inlet section 1, then expanded in the main body section 2 and then flows out through the outlet section 3, wherein: the gas working medium is transited from the inlet section 1 with a rectangular section channel to the main body section 2 with a conical channel in the flow channel.
In some preferred embodiments, the inlet of the nozzle is in the form of a straight circular arc blade, and the gas working medium enters the inlet section 1 through the inlet.
It can be understood that, because the inlet of the nozzle adopts a linear arc blade shape, the inlet end has a larger arc angle r to adapt to the change of the direction of the introduced gas flow, and in order to reduce the friction loss of the inlet and avoid the separation of the gas flow.
It can be understood that, because the main body section 2 is the main part of the gas expansion, compared with the original blade-shaped rectangular section channel, under the conditions of the same cross-sectional area, the same channel length and the same flow, the on-way loss coefficient of the conical channel is small, the energy loss is small, the speed coefficient of the nozzle can be effectively improved, and the isentropic efficiency of the turboexpander is improved.
In some preferred embodiments, the cone angle a of the conical channel is 9-13 degrees, the cone angle is too large, the air flow speed is not uniform in the pipeline, the wall surface is easy to generate air flow separation, the flow resistance of the air flow in the pipeline is increased, and the efficiency is reduced; the taper angle is too small, the change of the cross section area of the nozzle is too small, the air flow is not fully expanded in the nozzle, and the efficiency is reduced.
Referring again to fig. 1, the ratio of the throat width D of the nozzle to the length L of the cone is about 1:3, so that the velocity of the gas stream exiting from the outlet section 3 is more uniform.
It will be appreciated that the size of the throat width D of the nozzle is corrected by the three-dimensional design.
It will be appreciated that the exit radius R of the nozzle is determined by the radius of the impeller and the size of the radial gap between the nozzle and the impeller.
In addition, the invention also provides a low-temperature turboexpander comprising the nozzle.
The nozzle provided by the invention replaces the original blade-shaped nozzle with the spray pipe of the conical channel, combines the advantages of the linear arc blade-shaped nozzle, adopts the linear arc blade-shaped at the inlet and is transited into the conical channel. Compared with the rectangular section channel of the original blade profile, the conical channel has small on-way loss coefficient and energy loss under the conditions of same section area, same channel length and same flow, and can effectively improve the speed coefficient of the nozzle, so that the isentropic efficiency of the turboexpander is improved.
The technical features of the embodiments described above may be arbitrarily combined, and for the sake of brevity, all possible combinations of the technical features in the embodiments described above are not described, but should be considered as being within the scope of the present specification as long as there is no contradiction between the combinations of the technical features.
Of course, the nozzle cathode material of the present invention may have various changes and modifications, and is not limited to the specific structure of the above-described embodiment. In conclusion, the scope of the present invention should include those changes or substitutions and modifications which are obvious to those of ordinary skill in the art.
Claims (6)
1. A nozzle, comprising: an inlet section, a main body section and an outlet section, a gas working medium being introduced into said main body section through said inlet section, being expanded in said main body section and then flowing out through said outlet section, wherein: the gas working medium is transited from the inlet section of the channel with the rectangular cross section to the main body section of the conical channel in the flow channel.
2. The nozzle of claim 1 wherein said nozzle inlet is in the form of a straight circular arc blade and said gaseous working substance enters said inlet section through said inlet.
3. A nozzle as claimed in claim 1, wherein the conical passage has a cone angle a of 9 to 13 degrees.
4. A low temperature turboexpander comprising a nozzle, said nozzle comprising an inlet section, a main section and an outlet section, a gaseous working fluid being introduced into said main section through said inlet section and exiting through said outlet section after having been expanded in said main section, wherein: the gas working medium is transited from the inlet section of the channel with the rectangular cross section to the main body section of the conical channel in the flow channel.
5. The cryogenic turboexpander of claim 4, wherein said nozzle inlet is a straight circular arc blade profile, and said gaseous working fluid enters said inlet section through said inlet.
6. The cryogenic turboexpander of claim 4, wherein the conical passage has a cone angle a of 9 to 13 degrees.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911156194.3A CN112832871A (en) | 2019-11-22 | 2019-11-22 | Nozzle and low-temperature turbo expander |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911156194.3A CN112832871A (en) | 2019-11-22 | 2019-11-22 | Nozzle and low-temperature turbo expander |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112832871A true CN112832871A (en) | 2021-05-25 |
Family
ID=75922683
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911156194.3A Pending CN112832871A (en) | 2019-11-22 | 2019-11-22 | Nozzle and low-temperature turbo expander |
Country Status (1)
| Country | Link |
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| CN (1) | CN112832871A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB190515968A (en) * | 1904-08-06 | 1906-01-11 | George Westinghouse | Improvements in Elastic Fluid Turbines. |
| RU2010107153A (en) * | 2010-02-26 | 2011-09-10 | Федеральное государственное унитарное предприятие "Государственный космический научно-производственный центр имени М.В. Хруничева" (RU) | ACTIVE TURBINE NOZZLE DEVICE |
| 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 |
| CN108798790A (en) * | 2017-04-26 | 2018-11-13 | 中国航发商用航空发动机有限责任公司 | Blade profile tube nozzle for gas turbine |
| CN110043323A (en) * | 2019-05-16 | 2019-07-23 | 广东索特能源科技有限公司 | A kind of supersonic speed radial-inward-flow turbine |
-
2019
- 2019-11-22 CN CN201911156194.3A patent/CN112832871A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB190515968A (en) * | 1904-08-06 | 1906-01-11 | George Westinghouse | Improvements in Elastic Fluid Turbines. |
| RU2010107153A (en) * | 2010-02-26 | 2011-09-10 | Федеральное государственное унитарное предприятие "Государственный космический научно-производственный центр имени М.В. Хруничева" (RU) | ACTIVE TURBINE NOZZLE DEVICE |
| CN108798790A (en) * | 2017-04-26 | 2018-11-13 | 中国航发商用航空发动机有限责任公司 | Blade profile tube nozzle for gas turbine |
| 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 |
| CN110043323A (en) * | 2019-05-16 | 2019-07-23 | 广东索特能源科技有限公司 | A kind of supersonic speed radial-inward-flow turbine |
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