CN214660512U - Composite tangential air inlet transition section component of small gas turbine - Google Patents
Composite tangential air inlet transition section component of small gas turbine Download PDFInfo
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- CN214660512U CN214660512U CN202120840667.8U CN202120840667U CN214660512U CN 214660512 U CN214660512 U CN 214660512U CN 202120840667 U CN202120840667 U CN 202120840667U CN 214660512 U CN214660512 U CN 214660512U
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Abstract
The utility model relates to a transition section component of composite tangential air inlet of a small-sized gas turbine, which comprises an outer cylinder body, an inner cavity body, a centrifugal compressor, an axial-flow type power turbine and a combustion chamber; a transition section is arranged between the centrifugal compressor and the axial-flow type power turbine, a combustion chamber is tangentially arranged along the periphery of the transition section, and the transition section wraps part of the axial-flow type power turbine; the transition section is of a double-layer structure and comprises an outer cylinder body and an inner cavity, a high-temperature incoming flow channel of a combustion chamber is arranged in the inner cavity, and an incoming flow channel of a gas compressor is arranged between the inner cavity and the outer cylinder body; the centrifugal compressor is communicated with the combustion chamber through a compressor incoming flow channel; the combustor is communicated with the axial flow type power turbine through a high-temperature incoming airflow channel of the combustor. The utility model has the advantages that: the utility model discloses carry out the intensification design of structure, rational utilization centrifugal compressor and axial-flow type power turbine's structural feature designs compound changeover portion structure butt joint centrifugal compressor and wraps up axial-flow type power turbine, realizes the volume minimum.
Description
Technical Field
The utility model relates to a gas turbine, concretely relates to transition section part that small-size gas turbine's compound tangential was admitted air.
Background
The gas turbine is used as an internal combustion type power machine which takes continuous flowing gas as a working medium to drive an impeller to rotate so as to convert chemical energy into work, and comprises three large core parts: a compressor, a combustion chamber and a gas turbine. The gas compressor compresses air into high-pressure gas, the compressed gas enters the combustion chamber to be mixed with fuel to be combusted to form high-temperature and high-pressure gas, the high-temperature and high-pressure gas enters the gas turbine to expand to do work, and the gas turbine rotates to drive the gas compressor and simultaneously outputs mechanical work to drive the generator and the like. Different from the application occasions of large-scale gas turbine engines, the small-scale gas turbine engines are used in small scenes such as power supply and heat supply of buildings, and have simple structures and higher requirements on the integration of the gas turbine engines.
The large-scale gas turbine combustion chamber is large in number, is arranged around a central shaft in a circumferential mode, introduces high-temperature gas into a turbine inlet through a specific transition section structure, and the general embodiment is shown in figure 4, and relevant patents are as follows: the cooling mechanism of the gas turbine combustor transition section and the gas turbine combustor (CN204082339U) are characterized in that a guide shell is arranged on the back of a transition section body to form a cooling channel, one end of a gas guide pipe is connected with the guide shell, the other end of the gas guide pipe is connected between stages of a gas compressor, compressed air in the gas compressor is guided into the guide shell to cool the back of the transition section body in a convection mode, cooling of the back of the transition section is enhanced, and meanwhile, air inlet of a diffuser arranged below the belly of the transition section body impacts on the belly of the transition section to cool the belly of the transition section. In fig. 4: 1. a diffuser; 2. a transition section body; 3. a combustion cylinder; 4. a flame tube; 5. a first-stage turbine stator blade; 6. the transition section body belly; 7. the back of the transition section body; 8. a flow-guiding housing; 9. a cooling channel; 10. a bleed pipe; 11. air volume governing valve.
However, the large gas turbine compressor is basically axial-flow compressor, and because of the small inter-stage pressure ratio, the number of general stages is large, so the equipment is complex and large, and based on the intensive requirement of the small gas turbine, centrifugal compressor is generally adopted to ensure the basic pressure ratio and the requirement of the appearance is small, but the centrifugal compressor conflicts with the conventional multi-combustion-chamber arrangement scheme, so a better scheme needs to be found.
SUMMERY OF THE UTILITY MODEL
The utility model aims at overcoming the not enough among the prior art, provide a transition section part that small-size gas turbine's compound tangential was admitted air.
The transition section component of the composite tangential air inlet of the small-sized gas turbine comprises an outer cylinder body, an inner cavity body, a centrifugal compressor, an axial-flow type power turbine and a combustion chamber; a transition section is arranged between the centrifugal compressor and the axial-flow type power turbine, a combustion chamber is tangentially arranged along the periphery of the transition section, and the transition section wraps part of the axial-flow type power turbine; the transition section is of a double-layer structure and comprises an outer cylinder body and an inner cavity, a high-temperature incoming flow channel of a combustion chamber is arranged in the inner cavity, and an incoming flow channel of a gas compressor is arranged between the inner cavity and the outer cylinder body; the centrifugal compressor is communicated with the combustion chamber through a compressor incoming flow channel; the combustor is communicated with the axial flow type power turbine through a high-temperature incoming airflow channel of the combustor.
Preferably, the method comprises the following steps: and a cooling hole is formed at the position wrapping the axial flow type power turbine, and the cooling hole is a hole leading an air compressor flow channel to the inside of the axial flow type power turbine.
Preferably, the method comprises the following steps: a partition plate is arranged between the centrifugal compressor and the compressor airflow channel, and a cooling hole is formed in the bottom of the partition plate and is a hole of the compressor airflow channel leading to a central rotor of the axial-flow type power turbine.
Preferably, the method comprises the following steps: the inner cavity is a tapered structure leading from the combustion chamber to the axial flow power turbine.
Preferably, the method comprises the following steps: the joint of the combustion chamber and the inner cavity is provided with a plurality of supporting connecting pieces which are plug-in type double-layer supporting connecting pieces, the double-layer ends of the supporting connecting pieces are plug-in connected with the inner cavity, and the single-layer ends of the supporting connecting pieces are matched and clamped with the inner cylinder of the combustion chamber.
Preferably, the method comprises the following steps: the inner wall of the outer cylinder body and the outer wall of the inner cavity body are provided with fins.
Preferably, the method comprises the following steps: the inner wall of the inner cavity is coated with TBC coating.
Preferably, the method comprises the following steps: a combustion chamber connecting port is arranged between the transition section and the combustion chamber, and the combustion chamber connecting port is tangentially arranged along the periphery of the transition section.
Preferably, the method comprises the following steps: two combustion chambers which are arranged at 180 degrees are arranged on two sides of the transition section, or only a single combustion chamber is arranged, or more than three combustion chambers are uniformly arranged along the circumferential direction of the transition section.
The utility model has the advantages that:
1. the utility model discloses carry out the intensification design of structure, rational utilization centrifugal compressor and axial-flow type power turbine's structural feature designs compound changeover portion structure butt joint centrifugal compressor and wraps up axial-flow type power turbine, realizes that the volume is minimum, satisfies small-size gas turbine's intensification design requirement.
2. The utility model discloses combine centrifugal compressor export and changeover portion together, the maximum cooling changeover portion, this structural style's changeover portion wall area is big, requires high to the cooling, and this compressor can the cooling protection changeover portion wall of maximum to the mode that the combustion chamber runner and combustion chamber to turbine runner combined organically.
3. The utility model discloses the combustion chamber is to arranging on single changeover portion, and the high-temperature gas that the combustion chamber that the tangential was arranged produced can produce certain rotation naturally in the rotation of the circular structure of single changeover portion, has the back of rotation, and one-level stator blade in the axial-flow type power turbine more has the margin when designing the water conservancy diversion effect.
Drawings
FIG. 1 is a schematic diagram of a composite tangential inlet transition section component of a small gas turbine;
FIG. 2 is a schematic sectional view taken along line A-A of FIG. 1;
FIG. 3 is a schematic view of the installation of a plug-in double-deck bracing link;
FIG. 4 is a schematic diagram of an embodiment of a prior art gas turbine.
Description of reference numerals: the device comprises an outer cylinder body 1, an inner cavity 2, a partition plate 3, a supporting connecting piece 4, a centrifugal compressor 5, an axial-flow type power turbine 6, a combustion chamber 7 and an inserting position 8.
Detailed Description
The present invention will be further described with reference to the following examples. The following description of the embodiments is merely provided to aid in understanding the invention. It should be noted that, for those skilled in the art, without departing from the principle of the present invention, the present invention can be further modified and modified, and such modifications and modifications also fall within the protection scope of the appended claims.
Example one
The embodiment of the application provides a composite tangential air inlet transition section component of a small-sized gas turbine, and intensive design of a centrifugal compressor, a combustion chamber and an axial-flow type power turbine is realized through a unique structural form, as shown in fig. 1. The structure of the device comprises an outer cylinder body 1, an inner cavity body 2, a centrifugal compressor 5, an axial flow type power turbine 6 and a combustion chamber 7; a transition section is arranged between the centrifugal compressor 5 and the axial-flow type power turbine 6, a combustion chamber is tangentially arranged along the periphery of the transition section, and the transition section wraps part of the axial-flow type power turbine 6; the transition section is of a double-layer structure and comprises an outer cylinder body 1 and an inner cavity 2, a high-temperature incoming flow channel of a combustion chamber is arranged inside the inner cavity 2, and an incoming flow channel of a gas compressor is arranged between the inner cavity 2 and the outer cylinder body 1; the centrifugal compressor 5 is communicated with the combustion chamber 7 through a compressor incoming flow channel; the combustor 7 is in communication with the axial flow power turbine 6 through a combustor high temperature incoming airflow path. The outer diameter of the matched centrifugal compressors 5 is far larger than that of the axial-flow power turbine 6, so that the double-layer structure is designed, and the outer cylinder body 1 is combined with the inner cavity body 2.
In a preferred embodiment, the position surrounding the axial flow power turbine is provided with cooling holes for cooling the blade tip or cooling the hollow blade, the cooling holes are holes for the compressor incoming air to flow to the inside of the axial flow power turbine, the outside cold air (i.e. the compressor incoming air) is led to the blade tip of the power turbine through the cooling holes to cool the blade tip, and the cooling holes are led to the hollow blade, wherein the blade tip and the hollow blade are components inside the axial flow power turbine. A partition plate 3 is arranged between the centrifugal compressor 5 and the compressor inflow channel and used for partitioning the centrifugal compressor 5 and the compressor inflow channel, a cooling hole used for cooling a central rotor is formed in the bottom of the partition plate 3, the cooling hole is a hole of the compressor inflow channel leading to the central rotor of the axial-flow type power turbine and used for cooling a rotating part, the central rotor is a rotating part in the center of the axial-flow type power turbine, and the rotating part comprises a central rotating shaft, a centrifugal impeller of the central rotating shaft, a turbine disc of the axial-flow type power turbine and the like. The existence of the cooling holes enables part of the gas of the compressor incoming gas to flow around the inner cavity, and the main high-pressure incoming gas of the compressor flows to the combustion chamber through the connection ports of the combustion chambers which are arranged at 180 degrees on two sides to participate in the combustion of the gas, as shown in figure 2. The high-temperature incoming gas of the combustion chamber enters the inner cavity 2 through the inlet of the high-temperature incoming gas flow channel of the combustion chamber in the center of the outlet of the incoming gas flow channel of the two gas compressors, and the designed tapered structure accelerates the high-temperature incoming gas of the combustion chamber to rush to blades of the axial-flow power turbine from the inner cavity to complete work.
As a preferred embodiment, two supporting connectors 4 are provided at the junction of the combustion chamber and the inner cavity for the sake of assemblability, as shown in FIG. 2, for connecting the inner cylinder of the combustion chamber and the inner cavity. The supporting connecting piece 4 is a plug-in type double-layer supporting connecting piece, the double-layer end of the supporting connecting piece 4 is in plug-in connection with the inner cavity 2, and the single-layer end of the supporting connecting piece 4 is in matched clamping connection with the inner cylinder of the combustion chamber. The supporting connecting piece is taken off, the inner cavity body can be smoothly taken out of the outer cylinder body, and therefore interference cannot occur during assembly.
As a preferred embodiment, a certain amount of fins can be added on the inner wall of the outer cylinder 1 and the outer wall of the inner cavity 2 to enhance cooling, and TBC coating can be coated on the inner cavity to protect the wall surface.
As a preferred embodiment, as shown in fig. 2, a combustion chamber connection port is provided between the transition section and the combustion chamber 7, the combustion chamber connection port being arranged tangentially along the outer circumference of the transition section. Two combustion chambers which are arranged at 180 degrees are arranged on two sides of the transition section, and a single combustion chamber or a plurality of combustion chambers which are uniformly distributed along the circumferential direction can be arranged, so that the same effect can be achieved.
Example two
The second embodiment of the application provides a working method of a composite tangential air inlet transition section component of a small-sized gas turbine, which comprises the following steps: the incoming gas of the gas compressor flows in an incoming gas flow channel of the gas compressor in a way of wrapping the inner cavity 2, part of the incoming gas of the gas compressor enters the axial-flow type power turbine 6 through cooling holes to cool the internal components of the axial-flow type power turbine, the high-pressure incoming gas of the main gas compressor flows to the combustion chamber 7 through a combustion chamber connecting port arranged along the periphery of the transition section in a tangential way to participate in combustion of the gas, the high-temperature incoming gas of the combustion chamber enters the inner cavity 2 through a high-temperature incoming gas flow channel inlet of the combustion chamber, the high-temperature incoming gas of the combustion chamber is accelerated to rush to blades of the axial-flow type power turbine 6 to complete work through a tapered structure, and the high-temperature incoming gas entering the combustion chamber of the axial-flow type power turbine 6 has certain rotation.
Compared with the prior structural scheme, (1) the cooling protection of the cold air of the compressor to the wall surface of the transition section can be well realized; (2) the power turbine part in the axial flow type power turbine can be wrapped in the transition section to meet the intensification requirement; (3) the single transition section is tangentially arranged on the two sides of the combustion chamber, and the high-temperature gas at the outlet is provided with prerotation, so that the design of a power turbine blade is facilitated.
The utility model discloses a changeover portion design is based on centrifugal compressor and axial-flow type power turbine framework's structural component, and what can be reasonable utilizes microthermal compressor to come the gas and realize the cooling protection to the changeover portion wall, and utilizes reasonable structural design to avoid the centrifugal compressor external diameter to be greater than the space waste that the axial-flow type power turbine external diameter caused to satisfy small-size gas turbine's intensification requirement, reduce the gas turbine volume. The double combustion chambers which are arranged on a single transition section at 180 degrees are in the structural form of the transition section, so that high-temperature gas at the outlet of the combustion chambers passes through the transition section to form gas with a certain rotation degree to enter the power turbine, and the design of blades of the power turbine is favorable.
Claims (9)
1. A composite tangential entry transition piece for a small gas turbine engine, comprising: comprises an outer cylinder body (1), an inner cavity body (2), a centrifugal compressor (5), an axial-flow type power turbine (6) and a combustion chamber (7); a transition section is arranged between the centrifugal compressor (5) and the axial-flow type power turbine (6), a combustion chamber is tangentially arranged along the periphery of the transition section, and the transition section wraps part of the axial-flow type power turbine (6); the transition section is of a double-layer structure and comprises an outer cylinder body (1) and an inner cavity (2), a combustion chamber high-temperature incoming flow channel is arranged inside the inner cavity (2), and a gas compressor incoming flow channel is arranged between the inner cavity (2) and the outer cylinder body (1); the centrifugal compressor (5) is communicated with the combustion chamber (7) through a compressor airflow channel; the combustion chamber (7) is communicated with the axial flow type power turbine (6) through a high-temperature incoming airflow channel of the combustion chamber.
2. The small gas turbine compound tangential inlet transition piece component of claim 1, wherein: and a cooling hole is formed at the position wrapping the axial flow type power turbine, and the cooling hole is a hole leading an air compressor flow channel to the inside of the axial flow type power turbine.
3. The small gas turbine compound tangential inlet transition piece component of claim 1, wherein: a partition plate (3) is arranged between the centrifugal compressor (5) and the compressor inflow channel, and a cooling hole is formed in the bottom of the partition plate (3) and is a hole of the compressor inflow channel leading to a central rotor of the axial-flow type power turbine.
4. The small gas turbine compound tangential inlet transition piece component of claim 1, wherein: the inner cavity (2) is a tapered structure leading from the combustion chamber (7) to the axial-flow power turbine (6).
5. The small gas turbine compound tangential inlet transition piece component of claim 1, wherein: the joint of the combustion chamber (7) and the inner cavity (2) is provided with a plurality of supporting connecting pieces (4), the supporting connecting pieces (4) are plug-in double-layer supporting connecting pieces, the double-layer ends of the supporting connecting pieces (4) are plug-in connected with the inner cavity (2), and the single-layer ends of the supporting connecting pieces (4) are matched and clamped with the inner cylinder of the combustion chamber.
6. The small gas turbine compound tangential inlet transition piece component of claim 1, wherein: fins are arranged on the inner wall of the outer cylinder body (1) and the outer wall of the inner cavity (2).
7. The small gas turbine compound tangential inlet transition piece component of claim 1, wherein: the inner wall of the inner cavity (2) is coated with TBC coating.
8. The small gas turbine compound tangential inlet transition piece component of claim 1, wherein: a combustion chamber connecting port is arranged between the transition section and the combustion chamber (7), and the combustion chamber connecting port is tangentially arranged along the periphery of the transition section.
9. The small gas turbine compound tangential inlet transition piece component of claim 1, wherein: two combustion chambers which are arranged at 180 degrees are arranged on two sides of the transition section, or only a single combustion chamber is arranged, or more than three combustion chambers are uniformly arranged along the circumferential direction of the transition section.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202120840667.8U CN214660512U (en) | 2021-04-23 | 2021-04-23 | Composite tangential air inlet transition section component of small gas turbine |
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| CN202120840667.8U CN214660512U (en) | 2021-04-23 | 2021-04-23 | Composite tangential air inlet transition section component of small gas turbine |
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| CN214660512U true CN214660512U (en) | 2021-11-09 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113107679A (en) * | 2021-04-23 | 2021-07-13 | 浙江浙能技术研究院有限公司 | Transition section part for composite tangential air inlet of small gas turbine |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113107679A (en) * | 2021-04-23 | 2021-07-13 | 浙江浙能技术研究院有限公司 | Transition section part for composite tangential air inlet of small gas turbine |
| CN113107679B (en) * | 2021-04-23 | 2023-09-19 | 浙江浙能技术研究院有限公司 | Transition section component of composite tangential air inlet of small-sized gas turbine |
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