CN109113871B - Gas turbine of the regenerative type - Google Patents
Gas turbine of the regenerative type Download PDFInfo
- Publication number
- CN109113871B CN109113871B CN201811194879.2A CN201811194879A CN109113871B CN 109113871 B CN109113871 B CN 109113871B CN 201811194879 A CN201811194879 A CN 201811194879A CN 109113871 B CN109113871 B CN 109113871B
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- shell
- inlet
- cavity
- outlet
- air passage
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- 230000001172 regenerating effect Effects 0.000 title claims abstract description 25
- 238000002485 combustion reaction Methods 0.000 claims abstract description 50
- 238000007789 sealing Methods 0.000 claims abstract description 50
- 239000012530 fluid Substances 0.000 claims abstract description 13
- 230000002093 peripheral effect Effects 0.000 claims description 12
- 238000005265 energy consumption Methods 0.000 abstract description 4
- 239000007789 gas Substances 0.000 description 51
- 239000000446 fuel Substances 0.000 description 4
- 239000002737 fuel gas Substances 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 239000002918 waste heat Substances 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/08—Heating air supply before combustion, e.g. by exhaust gases
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/28—Arrangement of seals
Abstract
The invention discloses a regenerative gas turbine, which is characterized in that a regenerator, a combustion chamber, a gas compressor and a turbine are connected and fixed together through an inner shell, an outer shell and the like, wherein the inner shell, the outer shell, the regenerator, the combustion chamber and the like form a natural cold inlet cavity, a natural cold outlet cavity, a natural hot inlet cavity and a natural hot outlet cavity, and the inner sealing ring separates the cold inlet cavity from the cold outlet cavity, and the outer sealing ring separates the hot inlet cavity from the hot outlet cavity. The backheating type gas turbine has the advantages of compact overall structure, reasonable layout, small fluid pressure loss, reduced energy consumption, and avoidance of complex structures such as an external connecting pipeline between the backheating device and the gas turbine.
Description
Technical Field
The invention relates to a gas turbine, in particular to a regenerative gas turbine.
Background
A Gas Turbine (Gas Turbine) is a rotary power machine which uses continuously flowing Gas as a working medium to convert the heat energy of the working medium into mechanical work. Taking a simple cycle gas turbine as an example, the gas turbine mainly comprises a gas compressor, a combustion chamber and a turbine, and the working process is as follows: the air compressor sucks air from the atmosphere and compresses the air, the compressed air enters the combustion chamber and is mixed with the injected fuel to generate high-temperature fuel gas, the high-temperature fuel gas flows into the turbine to perform expansion work, the turbine is pushed to rotate to convert heat energy into rotating mechanical energy to be output, the gas after work is directly discharged into the atmosphere, and the temperature of the discharged fuel gas can still reach 500-700 ℃. In order to improve the energy utilization efficiency, a regenerative gas turbine is developed, which comprises a gas compressor, a combustion chamber and a turbine, and a regenerator, wherein compressed air is heated by exhaust waste heat through the regenerator, so that the consumption of fuel in the combustion chamber is reduced, and the energy utilization efficiency is improved.
The problems of the prior art are: because the arrangement position of the heat regenerator is not limited, compressed air coming out of a compressor outlet is generally communicated with a cold flow channel of the heat regenerator through a pipeline, or fuel gas coming out of a turbine outlet is communicated with a hot flow channel of the heat regenerator through a pipeline, and the heat regenerator is limited by the diameter and the length of the pipeline, so that the fluid pressure loss is large, the energy consumption is increased, and the whole structure of the gas turbine is not compact, uncooled and huge in volume.
Disclosure of Invention
The invention aims to solve the technical problem of providing a regenerative gas turbine which is compact in integral structure and small in fluid pressure loss.
In order to solve the technical problems, the regenerative gas turbine provided by the invention comprises a regenerator 13, a gas compressor 10, a combustion chamber 12, a turbine 11, an inner shell, an outer shell 9, an inner sealing ring 25 and an outer sealing ring 21;
the combustion chamber 12 is an annular cavity;
the heat regenerator 13 is annular and sleeved outside the combustion chamber 12;
the inner shell comprises a left shell 81, a middle shell 82 and a right shell 83;
the heat regenerator 13 and the combustion chamber 12 are fixed in the inner shell;
the middle shell 82 is in a circular tube shape and is sleeved outside the heat regenerator 13 in a ring shape;
the left shell 81 is annular, the left shell 81 is positioned at the left side of the heat regenerator 13 and the combustion chamber 12, the outer peripheral end of the left shell 81 is in sealing connection with the left end of the middle shell 82, and the inner peripheral end of the left shell 81 is in sealing connection with the shell of the compressor 10;
the right shell 83 is annular, the right shell 83 is positioned on the right side of the regenerator 13, the right side of the annular cavity of the combustion chamber 12 and the inner side of the inner ring side wall of the annular cavity, the outer peripheral end of the right shell 83 is in sealing connection with the right end of the middle shell 82, and the inner peripheral end of the right shell 83 is in sealing connection with the inner ring side wall of the annular cavity of the combustion chamber 12;
an inner sealing ring 25 is positioned between the heat regenerator 13 and the combustion chamber 12, and the inner sealing ring 25 surrounds the combustion chamber 12;
the outer ring seal 21 is positioned between the middle shell 82 and the heat regenerator 13, and the outer ring seal 21 surrounds the heat regenerator 13;
the heat regenerator 13 is provided with an axially arranged air passage and a radially arranged air passage which are isolated from each other;
the left shell 81, the left end of the regenerator 13, the left outer side wall of the annular cavity of the combustion chamber 12, the left part of the middle shell 82 and the left end of the inner sealing ring 25 together form a cold flow inlet chamber AA;
the air outlet of the air compressor 10 is communicated with the cold flow inlet cavity AA;
the right shell 83, the right end of the regenerator 13, the outer side wall of the right part of the combustion chamber 12, the right part of the middle shell 82 and the right end of the inner sealing ring 25 together form a cold outflow cavity BB;
an air inlet used for communicating the cold flow outlet cavity BB is arranged at the right part of the annular cavity of the combustion chamber 12;
the outer shell 9 is positioned outside the right shell 83, and the periphery of the outer shell 9 is in sealing connection with the right part of the middle shell 82;
the outer shell 9, the right shell 83, the middle shell 82, the right end of the outer sealing ring 21 and the outer side wall of the right part of the regenerator 13 together form a heat flow inlet cavity CC;
the high temperature gas outlet of the combustion chamber 12 is communicated with the gas inlet of the turbine 11, and the gas outlet of the turbine 11 is communicated with the hot flow inlet chamber CC.
Preferably, the regenerative gas turbine further comprises an intake header 30 and an exhaust header 31;
the heat regenerator 13 is provided with an air passage inlet which is axially arranged at the left end, an air passage outlet which is axially arranged at the right end, an air passage inlet which is radially arranged at the outer circumferential surface of the right part, and an air passage outlet which is radially arranged at the outer circumferential surface of the left part;
the cold inflow cavity AA is communicated with the axially arranged air passage inlet; the cold flow outlet cavity BB is communicated with the axially arranged air passage outlet; the heat flow inlet cavity CC is communicated with the radially arranged air passage inlet;
the left shell 81, the middle shell 82, the left end of the outer sealing ring 21 and the outer side wall of the left part of the heat regenerator 13 jointly form a heat flow outlet cavity DD communicated with the radially arranged air passage outlet;
the air inlet header 30 is communicated with the inlet of the compressor 10;
the exhaust manifold 31 communicates with the hot fluid outlet chamber DD.
Preferably, the regenerative gas turbine further comprises an intake header 30 and an exhaust header 31;
the heat regenerator 13 is provided with an air passage inlet which is axially arranged at the right end, an air passage outlet which is axially arranged at the left end, an air passage outlet which is radially arranged at the outer circumferential surface of the right part, and an air passage inlet which is radially arranged at the outer circumferential surface of the left part;
the cold inflow cavity AA is communicated with the radially arranged air passage inlet; the cold flow outlet cavity BB is communicated with the radially arranged air passage outlet; the heat flow inlet cavity CC is communicated with the axially arranged air passage inlet;
the left shell 81, the middle shell 82, the left end of the outer sealing ring 21 and the outer side wall of the left part of the heat regenerator 13 jointly form a heat flow outlet cavity DD communicated with the outlet of the axially arranged air passage;
the air inlet header 30 is communicated with the inlet of the compressor 10;
the exhaust manifold 31 communicates with the hot fluid outlet chamber DD.
Preferably, the compressor is a radial compressor, an axial compressor or a mixed flow compressor.
Preferably, the turbine is a radial, axial or mixed flow turbine.
According to the regenerative gas turbine disclosed by the invention, the compressor 10 sucks air and pressurizes the air, then discharges compressed air into the cold flow inlet cavity AA, then enters the cold flow outlet cavity BB through the cold flow channel of the regenerator 13, then enters the combustion chamber 12 from the cold flow outlet cavity BB to be mixed with injected fuel and combusted, the combusted high-temperature gas flows into the turbine 11 to perform expansion work, and the high-temperature tail gas after work is discharged through the hot flow inlet cavity CC of the regenerator 13. In the process that compressed air passes through the cold flow channel of the heat regenerator 13 and high-temperature tail gas passes through the hot flow channel of the heat regenerator 13, the compressed air and the high-temperature tail gas exchange heat. According to the regenerative gas turbine, a regenerator, a combustion chamber, a gas compressor and a turbine are connected and fixed together through an inner shell, a natural cold flow inlet cavity AA, a natural cold flow outlet cavity BB, a natural hot flow inlet cavity CC and a natural hot flow outlet cavity DD are formed on the inner shell and the outer shell, the cold flow inlet cavity AA and the cold flow outlet cavity BB are isolated by an inner sealing ring 25, and the hot flow inlet cavity CC and the hot flow outlet cavity DD are isolated by an outer sealing ring 21. The gas turbine has the advantages of compact integral structure, reasonable layout, small fluid pressure loss, reduced energy consumption, and avoidance of complex structures such as external connecting pipelines between the heat regenerator and the gas turbine.
Drawings
In order to more clearly illustrate the technical solutions of the present invention, the following brief description of the drawings is given for the purpose of the present invention, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and that other drawings can be obtained according to these drawings without the need for inventive work for a person skilled in the art.
FIG. 1 is a schematic diagram of a cold flow path of an embodiment of a regenerative gas turbine of the present invention;
FIG. 2 is a schematic view of a heat flow path of an embodiment of a regenerative gas turbine of the present invention.
Reference numerals illustrate:
a gas compressor 10; a turbine 11; a 12 combustion chamber; 13 a regenerator; sealing the outer ring of the 21; 25 inner ring sealing; 30 inlet header; 31 an exhaust manifold; 81 left shell; 82 a middle housing; 83 right housing; 9 an outer shell; AA cold flow inlet chamber; BB cold flows out of the mouth; a CC heat flow inlet chamber; DD heat flows out of the mouth.
Detailed Description
The following description of the embodiments of the present invention will be made more apparent and fully hereinafter with reference to the accompanying drawings, in which some, but not all embodiments of the invention are shown. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
Example 1
As shown in fig. 1 and 2, the regenerative gas turbine includes a regenerator 13, a compressor 10, a combustion chamber 12, a turbine 11, an inner casing, an outer casing 9, an inner seal ring 25, and an outer seal ring 21;
the combustion chamber 12 is an annular cavity;
the heat regenerator 13 is annular and sleeved outside the combustion chamber 12;
the inner shell comprises a left shell 81, a middle shell 82 and a right shell 83;
the heat regenerator 13 and the combustion chamber 12 are fixed in the inner shell;
the middle shell 82 is in a circular tube shape and is sleeved outside the heat regenerator 13 in a ring shape;
the left shell 81 is annular, the left shell 81 is positioned at the left side of the heat regenerator 13 and the combustion chamber 12, the outer peripheral end of the left shell 81 is in sealing connection with the left end of the middle shell 82, and the inner peripheral end of the left shell 81 is in sealing connection with the shell of the compressor 10;
the right shell 83 is annular, the right shell 83 is positioned on the right side of the regenerator 13, the right side of the annular cavity of the combustion chamber 12 and the inner side of the inner ring side wall of the annular cavity, the outer peripheral end of the right shell 83 is in sealing connection with the right end of the middle shell 82, and the inner peripheral end of the right shell 83 is in sealing connection with the inner ring side wall of the annular cavity of the combustion chamber 12;
an inner sealing ring 25 is positioned between the heat regenerator 13 and the combustion chamber 12, and the inner sealing ring 25 surrounds the combustion chamber 12;
the outer ring seal 21 is positioned between the middle shell 82 and the heat regenerator 13, and the outer ring seal 21 surrounds the heat regenerator 13;
the heat regenerator 13 is provided with an axially arranged air passage and a radially arranged air passage which are isolated from each other;
the left shell 81, the left end of the regenerator 13, the left outer side wall of the annular cavity of the combustion chamber 12, the left part of the middle shell 82 and the left end of the inner sealing ring 25 together form a cold flow inlet chamber AA;
the air outlet of the air compressor 10 is communicated with the cold flow inlet cavity AA;
the right shell 83, the right end of the regenerator 13, the outer side of the right part of the combustion chamber 12, the right part of the middle shell 82 and the right end of the inner sealing ring 25 together form a cold outflow cavity BB;
an air inlet used for communicating the cold flow outlet cavity BB is arranged at the right part of the annular cavity of the combustion chamber 12;
the outer shell 9 is positioned outside the right shell 83, and the periphery of the outer shell 9 is in sealing connection with the right part of the middle shell 82;
the outer shell 9, the right shell 83, the middle shell 82, the right end of the outer sealing ring 21 and the outer side wall of the right part of the regenerator 13 together form a heat flow inlet cavity CC;
the high temperature gas outlet of the combustion chamber 12 is communicated with the gas inlet of the turbine 11, and the gas outlet of the turbine 11 is communicated with the hot flow inlet chamber CC.
In the regenerative gas turbine of the first embodiment, the compressor 10 sucks air and pressurizes the air, then discharges compressed air into the cold inflow cavity AA, then enters the cold outflow cavity BB through the cold flow channel of the regenerator 13, then enters the combustion chamber 12 from the cold flow outflow cavity BB to be mixed with injected fuel and combusted, the combusted high-temperature gas flows into the turbine 11 to perform expansion work, and the high-temperature tail gas after work enters the hot flow inflow cavity CC and then is discharged through the hot flow channel of the regenerator 13. In the process that compressed air passes through the cold flow channel of the heat regenerator 13 and high-temperature tail gas passes through the hot flow channel of the heat regenerator 13, the compressed air and the high-temperature tail gas exchange heat. According to the regenerative gas turbine, a regenerator, a combustion chamber, a gas compressor and a turbine are connected and fixed together through an inner shell, a natural cold flow inlet cavity AA, a natural cold flow outlet cavity BB, a natural hot flow inlet cavity CC and a natural hot flow outlet cavity DD are formed on the inner shell and the outer shell, the cold flow inlet cavity AA and the cold flow outlet cavity BB are isolated by an inner sealing ring 25, and the hot flow inlet cavity CC and the hot flow outlet cavity DD are isolated by an outer sealing ring 21. The gas turbine has the advantages of compact integral structure, reasonable layout, small fluid pressure loss, reduced energy consumption, and avoidance of complex structures such as external connecting pipelines between the heat regenerator and the gas turbine.
Example two
According to the first embodiment, the regenerative gas turbine further comprises an intake manifold 30 and an exhaust manifold 31;
the heat regenerator 13 is provided with an air passage inlet which is axially arranged at the left end, an air passage outlet which is axially arranged at the right end, an air passage inlet which is radially arranged at the outer circumferential surface of the right part, and an air passage outlet which is radially arranged at the outer circumferential surface of the left part;
the cold inflow cavity AA is communicated with the axially arranged air passage inlet; the cold flow outlet cavity BB is communicated with the axially arranged air passage outlet; the heat flow inlet cavity CC is communicated with the radially arranged air passage inlet;
the left shell 81, the middle shell 82, the left end of the outer sealing ring 21 and the outer side wall of the left part of the heat regenerator 13 jointly form a heat flow outlet cavity DD communicated with the radially arranged air passage outlet;
the air inlet header 30 is communicated with the inlet of the compressor 10;
the exhaust manifold 31 communicates with the hot fluid outlet chamber DD.
In the regenerative gas turbine of the second embodiment, the air passage is axially arranged as a cold flow passage and the air passage is radially arranged as a hot flow passage of the regenerator 13, and the cold flow path of the regenerative gas turbine is shown in fig. 1, the hot flow path is shown in fig. 2, the exhaust manifold 31 is communicated with the hot flow outlet chamber DD, and the outer seal ring 21 isolates the hot flow inlet chamber CC from the hot flow outlet chamber DD.
Example III
According to the first embodiment, the regenerative gas turbine further comprises an intake manifold 30 and an exhaust manifold 31;
the heat regenerator 13 is provided with an air passage inlet which is axially arranged at the right end, an air passage outlet which is axially arranged at the left end, an air passage outlet which is radially arranged at the outer circumferential surface of the right part, and an air passage inlet which is radially arranged at the outer circumferential surface of the left part;
the cold inflow cavity AA is communicated with the radially arranged air passage inlet; the cold flow outlet cavity BB is communicated with the radially arranged air passage outlet; the heat flow inlet cavity CC is communicated with the axially arranged air passage inlet;
the left shell 81, the middle shell 82, the left end of the outer sealing ring 21 and the outer side wall of the left part of the heat regenerator 13 jointly form a heat flow outlet cavity DD communicated with the outlet of the axially arranged air passage;
the air inlet header 30 is communicated with the inlet of the compressor 10;
the exhaust manifold 31 communicates with the hot fluid outlet chamber DD.
In the regenerative gas turbine of the third embodiment, the air passage is axially arranged in the regenerator 13 as a hot flow passage, and the air passage is radially arranged as a cold flow passage.
Example IV
The regenerative gas turbine according to the first embodiment, the compressor may be a radial compressor, an axial compressor, or a mixed flow compressor;
the turbine may be a radial, axial or mixed flow turbine.
The foregoing is merely a preferred embodiment of the present application and is not intended to limit the present application. Various modifications and changes may be made to the present application by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principles of the present application should be included in the protection scope of the present application.
Claims (5)
1. The regenerative gas turbine is characterized by comprising a regenerator (13), a gas compressor (10), a combustion chamber (12), a turbine (11), an inner shell, an outer shell (9), an inner sealing ring (25) and an outer sealing ring (21);
the combustion chamber (12) is an annular cavity;
the heat regenerator (13) is annular and sleeved outside the combustion chamber (12);
the inner shell comprises a left shell (81), a middle shell (82) and a right shell (83);
the heat regenerator (13) and the combustion chamber (12) are fixed in the inner shell;
the middle shell (82) is in a circular tube shape and is sleeved outside the heat regenerator (13);
the left shell (81) is annular, the left shell (81) is positioned at the left side of the heat regenerator (13) and the combustion chamber (12), the outer peripheral end of the left shell (81) is in sealing connection with the left end of the middle shell (82), and the inner peripheral end of the left shell (81) is in sealing connection with the shell of the compressor (10);
the right shell (83) is annular, the right shell (83) is positioned on the right side of the heat regenerator (13), the right side of the annular cavity of the combustion chamber (12) and the inner side of the inner ring side wall of the annular cavity, the outer peripheral end of the right shell (83) is in sealing connection with the right end of the middle shell (82), and the inner peripheral end of the right shell (83) is in sealing connection with the inner ring side wall of the annular cavity of the combustion chamber (12);
the inner sealing ring (25) is positioned between the heat regenerator (13) and the combustion chamber (12), and the inner sealing ring (25) surrounds the combustion chamber (12);
the outer sealing ring (21) is positioned between the middle shell (82) and the heat regenerator (13), and the outer sealing ring (21) surrounds the heat regenerator (13);
the heat regenerator (13) is provided with an axially arranged air passage and a radially arranged air passage which are mutually isolated;
the left shell (81), the left end of the heat regenerator (13), the left outer side wall of the annular cavity of the combustion chamber (12), the left part of the middle shell (82) and the left end of the inner sealing ring (25) form a cold flow inlet chamber (AA);
the air outlet of the air compressor (10) is communicated with the cold flow inlet cavity (AA);
the right shell (83), the right end of the heat regenerator (13), the outer side wall of the right part of the combustion chamber (12), the right part of the middle shell (82) and the right end of the inner sealing ring (25) form a cold outflow cavity (BB);
an air inlet used for communicating the cold flow outlet cavity (BB) is formed in the right part of the annular cavity of the combustion chamber (12);
the outer shell (9) is positioned at the outer side of the right shell (83), and the periphery of the outer shell (9) is connected with the right part of the middle shell (82) in a sealing way;
the outer shell (9), the right shell (83), the middle shell (82), the right end of the outer sealing ring (21) and the outer side wall of the right part of the heat regenerator (13) form a heat flow inlet cavity (CC);
the high-temperature gas outlet of the combustion chamber (12) is communicated with the gas inlet of the turbine (11), and the gas outlet of the turbine (11) is communicated with the hot flow inlet cavity (CC).
2. The backheating gas turbine of claim 1, wherein,
the regenerative gas turbine also comprises an air inlet header (30) and an air outlet header (31);
the heat regenerator (13) is provided with an air passage inlet which is axially arranged at the left end, an air passage outlet which is axially arranged at the right end, an air passage inlet which is radially arranged at the outer circumferential surface of the right part, and an air passage outlet which is radially arranged at the outer circumferential surface of the left part;
the cold inflow cavity (AA) is communicated with the axially arranged air passage inlet; the cold flow outlet cavity (BB) is communicated with the axially arranged air passage outlet; the hot fluid inlet chamber (CC) communicates with the radially arranged airway inlet;
the left shell (81), the middle shell (82), the left end of the outer sealing ring (21) and the outer side wall of the left part of the heat regenerator (13) jointly form a heat flow outlet cavity (DD) communicated with the outlet of the radially arranged air passage;
the air inlet header (30) is communicated with the inlet of the compressor (10);
the exhaust manifold (31) communicates with the hot fluid outlet chamber (DD).
3. The backheating gas turbine of claim 1, wherein,
the regenerative gas turbine also comprises an air inlet header (30) and an air outlet header (31);
the heat regenerator (13) is provided with an air passage inlet which is axially arranged at the right end, an air passage outlet which is axially arranged at the left end, an air passage outlet which is radially arranged at the outer circumferential surface of the right part, and an air passage inlet which is radially arranged at the outer circumferential surface of the left part;
the cold inflow cavity (AA) is communicated with the radially arranged air passage inlet; the cold flow outlet cavity (BB) is communicated with the radially arranged air passage outlet; the hot fluid inlet chamber (CC) communicates with the axially arranged airway inlet;
the left shell (81), the middle shell (82), the left end of the outer sealing ring (21) and the outer side wall of the left part of the heat regenerator (13) jointly form a heat flow outlet cavity (DD) communicated with the outlet of the axially arranged air passage;
the air inlet header (30) is communicated with the inlet of the compressor (10);
the exhaust manifold (31) communicates with the hot fluid outlet chamber (DD).
4. The backheating gas turbine of claim 1, wherein,
the compressor is a radial-flow compressor, an axial-flow compressor or a mixed-flow compressor.
5. The backheating gas turbine of claim 1, wherein,
the turbine is a radial flow, axial flow or mixed flow turbine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811194879.2A CN109113871B (en) | 2018-10-15 | 2018-10-15 | Gas turbine of the regenerative type |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811194879.2A CN109113871B (en) | 2018-10-15 | 2018-10-15 | Gas turbine of the regenerative type |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109113871A CN109113871A (en) | 2019-01-01 |
| CN109113871B true CN109113871B (en) | 2024-03-15 |
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ID=64854253
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811194879.2A Active CN109113871B (en) | 2018-10-15 | 2018-10-15 | Gas turbine of the regenerative type |
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4474000A (en) * | 1982-11-12 | 1984-10-02 | Williams International Corporation | Recuperated turbine engine |
| US5855112A (en) * | 1995-09-08 | 1999-01-05 | Honda Giken Kogyo Kabushiki Kaisha | Gas turbine engine with recuperator |
| JP2011163287A (en) * | 2010-02-12 | 2011-08-25 | Niigata Power Systems Co Ltd | Regenerative cycle gas turbine device |
| CN203702343U (en) * | 2014-03-06 | 2014-07-09 | 苟仲武 | Low-temperature hybrid power gas turbine |
| CN205823453U (en) * | 2016-06-16 | 2016-12-21 | 上海和兰透平动力技术有限公司 | It is capable of the small size gas turbine of extraction cycle |
| CN107044347A (en) * | 2017-05-23 | 2017-08-15 | 上海泛智能源装备有限公司 | A kind of regenerator and gas turbine |
| CN209083420U (en) * | 2018-10-15 | 2019-07-09 | 上海和兰透平动力技术有限公司 | Regenerative-type gas turbine |
-
2018
- 2018-10-15 CN CN201811194879.2A patent/CN109113871B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4474000A (en) * | 1982-11-12 | 1984-10-02 | Williams International Corporation | Recuperated turbine engine |
| US5855112A (en) * | 1995-09-08 | 1999-01-05 | Honda Giken Kogyo Kabushiki Kaisha | Gas turbine engine with recuperator |
| JP2011163287A (en) * | 2010-02-12 | 2011-08-25 | Niigata Power Systems Co Ltd | Regenerative cycle gas turbine device |
| CN203702343U (en) * | 2014-03-06 | 2014-07-09 | 苟仲武 | Low-temperature hybrid power gas turbine |
| CN205823453U (en) * | 2016-06-16 | 2016-12-21 | 上海和兰透平动力技术有限公司 | It is capable of the small size gas turbine of extraction cycle |
| CN107044347A (en) * | 2017-05-23 | 2017-08-15 | 上海泛智能源装备有限公司 | A kind of regenerator and gas turbine |
| CN209083420U (en) * | 2018-10-15 | 2019-07-09 | 上海和兰透平动力技术有限公司 | Regenerative-type gas turbine |
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| Publication number | Publication date |
|---|---|
| CN109113871A (en) | 2019-01-01 |
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