CN113294263A - Power machine with coaxial output of gas turbine and air turbine - Google Patents
Power machine with coaxial output of gas turbine and air turbine Download PDFInfo
- Publication number
- CN113294263A CN113294263A CN202110708490.0A CN202110708490A CN113294263A CN 113294263 A CN113294263 A CN 113294263A CN 202110708490 A CN202110708490 A CN 202110708490A CN 113294263 A CN113294263 A CN 113294263A
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- China
- Prior art keywords
- gas
- turbine
- air
- culvert
- turbofan
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
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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
- F01D13/00—Combinations of two or more machines or engines
- F01D13/02—Working-fluid interconnection of machines or engines
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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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/025—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the by-pass flow being at least partly used to create an independent thrust component
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
Abstract
The invention provides a power machine coaxially outputting a gas turbine and an air turbine, which is characterized in that: the gas turbine power turbine shaft and the air turbine shaft are connected through a coupling; the gas turbine consists of a turbofan gas generator and a power turbine matched with the turbofan gas generator, the turbofan gas generator is a retired turbofan aircraft engine with a tail nozzle and a boosting system removed, and the turbofan gas generator comprises a high-pressure gas compressor and a culvert channel of the high-pressure gas compressor. The gas heat exchanger is provided with two groups of air inlets and air outlets, one end of a high-pressure air delivery pipe and one end of a hot air output pipe of the outer culvert are respectively connected to the horizontal air inlet and the horizontal air outlet, the vertical air inlet is connected to the exhaust air outlet of the power turbine of the gas turbine, and the vertical air outlet is the exhaust air outlet of the heat exchanger; the other end of the bypass high-pressure gas pipe is connected to the tail part of a bypass channel of the turbofan gas generator, and the other end of the hot gas output pipe is connected to an air inlet of the air turbine.
Description
Technical Field
The invention relates to an aeroderivative gas turbine, in particular to a power machine coaxially outputting the aeroderivative gas turbine and an air turbine.
Background
The turbofan aircraft engine mainly comprises a low-pressure compressor, a high-pressure compressor, a bypass channel of the low-pressure compressor, a combustion chamber, a tail nozzle, a boosting system and the like, wherein most of pressure air generated by the low-pressure compressor is conveyed to the high-pressure compressor to do work, and the rest of pressure air enters the bypass channel of the high-pressure compressor. The engine works reliably and has a stable production line in China. Hundreds of engines in service have a great deal of potential retired engine resources, so that the retired turbofan aircraft engine is changed into a gas turbine, and the gas turbine has a wide development prospect. At present, the method for changing a turbofan aircraft engine into a gas turbine is to remove the bypass air of the turbofan aircraft engine, perform top cutting treatment on all rotor blades on a low-pressure air compressor to be used as a gas generator, and then match the rotor blades with a power turbine to form the gas turbine (namely, the top cutting gas turbine). Because the torsion angle of the top of each rotor blade of the topping gas turbine is large and the torsion angle of the root is small, after the top with the large torsion angle is cut off, although the power consumption of the low-pressure gas compressor is reduced, the efficiency of the low-pressure gas compressor, namely the topping gas turbine, is also greatly reduced; secondly, exhaust gas generated by the top-cutting gas generator after the power turbine does work is exhausted outwards from an exhaust gas outlet of the power turbine by high-temperature and high-pressure gas, and heat energy is still stored in the exhaust gas, so that the heat energy loss of the exhaust gas is caused.
Air turbines as mature prior art include air turbines and their shafts.
Disclosure of Invention
The invention aims to provide a power machine which can recover the exhaust heat energy and is coaxially output by a gas turbine and an air turbine.
The purpose of the invention is realized as follows: it includes gas turbine, characterized by: the gas turbine power turbine shaft and the air turbine shaft are connected through a coupler, so that the power turbine shaft and the air turbine shaft are coaxial, and the gas turbine power turbine shaft is also an output shaft of the gas turbine and is connected with a load; the gas turbine consists of a turbofan gas generator and a power turbine matched with the turbofan gas generator, the turbofan gas generator is an out-of-service turbofan aircraft engine with a tail nozzle and a thrust augmentation system removed, and the turbofan gas generator comprises a high-pressure compressor and a culvert channel of the high-pressure compressor.
The gas heat exchanger is provided with two groups of air inlets-air outlets, one group is a horizontal (direction) air inlet-air outlet, and the other group is a vertical (direction) air inlet-air outlet; one end of the outer culvert high-pressure gas pipe and one end of the hot gas output pipe are respectively connected to a horizontal air inlet and a horizontal air outlet, a vertical air inlet is connected to a gas turbine power turbine exhaust gas outlet, and the vertical air outlet is a heat exchanger exhaust gas outlet; the other end of the bypass high-pressure gas pipe is connected to the tail part of a bypass channel of the turbofan gas generator, and the other end of the hot gas output pipe is connected to an air inlet of the air turbine.
The working process of the gas turbine is the same as that of the topping gas turbine, and a power turbine drives a power turbine shaft to output rotating speed and torque (hereinafter referred to as power); on the other hand, bypass pressurized air is taken out from the tail part of a bypass channel of the turbofan gas generator, exhaust gas containing heat energy exhausted from an exhaust port of the power turbine exchanges heat with the gas heat exchanger to obtain bypass high-pressure hot gas, the bypass high-pressure hot gas is transmitted to the air turbine through a hot gas output pipe and serves as a driving source of the air turbine to drive the air turbine and a shaft of the air turbine to rotate, and the air turbine outputs power. Thus, the air turbine and the gas turbine simultaneously output power on one output shaft (coaxial).
Compared with a topping gas turbine, the invention has the following positive effects: the bypass supercharged air of the gas turbine and the exhaust gas of the power turbine are recycled as a driving source of the air turbine and output power together with the gas turbine, and under the condition of the same energy consumption, larger power output is obtained. Meanwhile, another modification scheme is provided for the retired aircraft engine, and the utilization rate of the retired aircraft engine is improved.
Drawings
The invention is further described below with reference to the accompanying drawings.
FIG. 1 is a schematic of the present invention.
Fig. 2 is a sectional view taken along line a-a of fig. 1.
Detailed Description
Referring to fig. 1, the gas turbine is composed of a turbofan gas generator 1 and a power turbine 4 matched with the turbofan gas generator, the turbofan gas generator is an retired turbofan aircraft engine without a tail nozzle and a boosting system, and the turbofan gas generator comprises a high-pressure compressor and a culvert channel thereof; the power turbine shaft of the gas turbine is connected with the air turbine shaft of the air turbine 11 through a coupler 8, so that the power turbine shaft and the air turbine shaft are coaxial and are also the output shaft 12 of the invention. 10 is the air turbine exhaust.
The air heat exchanger 5 is provided with two groups of air inlets and air outlets, one group is a horizontal air inlet and air outlet, and the other group is a vertical air inlet and air outlet; one end of the external culvert high-pressure gas pipe 3 and one end of the hot gas output pipe 9 are respectively connected to a horizontal air inlet and a horizontal air outlet, a vertical air inlet is connected to a gas turbine power turbine exhaust gas exhaust port 7, and the vertical air outlet is a heat exchanger exhaust gas exhaust port 6; the other end of the bypass high-pressure gas pipe is connected to the tail part of a bypass channel of the turbofan gas generator, and the other end of the hot gas output pipe is connected to an air inlet of the air turbine.
Referring to fig. 2, the fact that the other end of the bypass high-pressure gas pipe is connected to the tail of the bypass channel of the turbofan gas generator means that a plurality of bypass gas outlets 14 are uniformly formed on one circumference of the outer wall 13 of the tail of the bypass; secondly, an annular gas collection chamber 2 is arranged on the outer ring of the outer bypass gas outlet hole, the annular gas collection chamber 2 is welded on the outer wall 13 of the outer bypass casing, and the outer bypass gas is taken into the annular gas collection chamber 2 through a plurality of outer bypass gas outlet holes 14; the upper half circumference of the culvert gas collecting chamber is provided with a plurality of four pipe joints 15, the inner end of each pipe joint is communicated with the annular gas collecting chamber, the outer end of each pipe joint is connected with the other end of a culvert high-pressure gas conveying pipe, and the number of the culvert high-pressure gas conveying pipes is four. 16 is an outer culvert air passage, and 17 is an inner culvert high pressure compressor passage. The output shaft 12 of the present invention is connected to a load.
The working process of the gas turbine is the same as that of the topping gas turbine, and a power turbine drives a power turbine shaft to output rotating speed and torque; on the other hand, bypass pressurized air is taken out from the tail part of a bypass channel of the turbofan gas generator, exhaust gas containing heat energy exhausted from an exhaust port of the power turbine exchanges heat with the gas heat exchanger to obtain bypass high-pressure hot gas, the bypass high-pressure hot gas is transmitted to the air turbine through a hot gas output pipe and serves as a driving source of the air turbine to drive the air turbine and a shaft of the air turbine to rotate, and the air turbine outputs rotating speed and torque. Thus, the air turbine and the gas turbine output both rotational speed and torque on one shaft (coaxial).
Claims (2)
1. A power machine with coaxial output of a gas turbine and an air turbine comprises the gas turbine and is characterized in that: the gas turbine power turbine shaft is connected with the air turbine shaft of the air turbine through a coupler; the gas turbine consists of a turbofan gas generator and a power turbine matched with the turbofan gas generator, wherein the turbofan gas generator is a retired turbofan aircraft engine without a tail nozzle and a thrust augmentation system, and the turbofan gas generator comprises a high-pressure gas compressor and a culvert channel thereof;
the gas heat exchanger is provided with two groups of air inlets and air outlets, one group is a horizontal air inlet and an air outlet, and the other group is a vertical air inlet and an air outlet; one end of the outer culvert high-pressure gas pipe and one end of the hot gas output pipe are respectively connected to a horizontal air inlet and a horizontal air outlet, a vertical air inlet is connected to a gas turbine power turbine exhaust gas outlet, and the vertical air outlet is a heat exchanger exhaust gas outlet; the other end of the bypass high-pressure gas pipe is connected to the tail part of a bypass channel of the turbofan gas generator, and the other end of the hot gas output pipe is connected to an air inlet of the air turbine.
2. The gas turbine and air turbine co-axial output power machine as claimed in claim 1, wherein: the other end of the culvert high-pressure gas pipe is connected to the tail part of the culvert channel of the turbofan gas generator, namely, a plurality of culvert gas outlets are uniformly formed on one circumference of the outer wall of the tail part of the culvert; an annular gas collection chamber is arranged on the outer ring of the outer culvert gas outlet hole, is welded on the outer wall of the outer culvert casing, and takes the outer culvert gas into the annular gas collection chamber through a plurality of outer culvert gas outlet holes; the upper half circumference of the culvert gas collection chamber is provided with a plurality of four pipe joints, the inner end of each pipe joint is communicated with the annular gas collection chamber, the outer end of each pipe joint is connected with the other end of a culvert high-pressure gas conveying pipe, and the number of the culvert high-pressure gas conveying pipes is four.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110708490.0A CN113294263A (en) | 2021-06-25 | 2021-06-25 | Power machine with coaxial output of gas turbine and air turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110708490.0A CN113294263A (en) | 2021-06-25 | 2021-06-25 | Power machine with coaxial output of gas turbine and air turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113294263A true CN113294263A (en) | 2021-08-24 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110708490.0A Pending CN113294263A (en) | 2021-06-25 | 2021-06-25 | Power machine with coaxial output of gas turbine and air turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113294263A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113898472A (en) * | 2021-11-17 | 2022-01-07 | 上海电气燃气轮机有限公司 | Compressor modification method and compressor |
| CN114993638A (en) * | 2022-05-07 | 2022-09-02 | 中国联合重型燃气轮机技术有限公司 | Rotating turbine blade cooling test system and method |
| CN115450713A (en) * | 2022-10-21 | 2022-12-09 | 中国航发沈阳发动机研究所 | Evenly-exhausting bearing frame assembly structure |
-
2021
- 2021-06-25 CN CN202110708490.0A patent/CN113294263A/en active Pending
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113898472A (en) * | 2021-11-17 | 2022-01-07 | 上海电气燃气轮机有限公司 | Compressor modification method and compressor |
| CN113898472B (en) * | 2021-11-17 | 2023-06-13 | 上海电气燃气轮机有限公司 | Gas compressor retrofitting method and gas compressor |
| CN114993638A (en) * | 2022-05-07 | 2022-09-02 | 中国联合重型燃气轮机技术有限公司 | Rotating turbine blade cooling test system and method |
| CN115450713A (en) * | 2022-10-21 | 2022-12-09 | 中国航发沈阳发动机研究所 | Evenly-exhausting bearing frame assembly structure |
| CN115450713B (en) * | 2022-10-21 | 2023-01-17 | 中国航发沈阳发动机研究所 | Evenly-exhausting bearing frame assembly structure |
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