CN212177222U - Gas generator turbine upper end wall structure suitable for medium and small gas turbines - Google Patents
Gas generator turbine upper end wall structure suitable for medium and small gas turbines Download PDFInfo
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- CN212177222U CN212177222U CN202021097787.5U CN202021097787U CN212177222U CN 212177222 U CN212177222 U CN 212177222U CN 202021097787 U CN202021097787 U CN 202021097787U CN 212177222 U CN212177222 U CN 212177222U
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Abstract
A gas generator turbine upper end wall structure suitable for medium and small gas turbines belongs to the field of gas turbines. The utility model discloses a first order stationary blade, the turbine cylinder body, the first order moving blade, the movable vane retaining ring, the movable vane is held the ring, the ring is held to the length, the second level stationary blade, the second level moving blade, the first order stationary blade is connected the installation with the turbine cylinder body, the movable vane is held the ring and is connected the installation with the turbine cylinder body, the movable vane retaining ring is installed on the movable vane is held the ring, first honeycomb seal structure has been arranged between movable vane retaining ring and the first order moving blade, first honeycomb seal structure installs on the movable vane retaining ring, the long ring fixed mounting that holds is on the turbine cylinder body, the second level stationary blade passes through bolt fixed mounting and holds on the ring at the length, be provided with second honeycomb seal structure on the second level stationary blade. The utility model discloses research and development purpose is in order to solve the problem that the mainstream gas passageway's of gas turbine sealed and the upper end wall is compact to be connected, the utility model discloses simple structure, design benefit, easy dismounting, equipment are firm.
Description
Technical Field
The utility model relates to a gas generator turbine upper end wall structure suitable for middle and small combustion engine belongs to the gas turbine field.
Background
At present, for a gas turbine unit, the safety and the structural design of the unit are also particularly important when the efficiency of the gas turbine is improved, and the improvement of the turbine efficiency not only needs advanced blade design but also needs a reasonable upper end wall connecting structure. A large number of gaps are reserved between the seal of a main stream gas channel and an upper end wall structure of a medium and small-sized gas turbine which is widely used at present, the pneumatic efficiency of the gas turbine is greatly reduced by the gaps, the service life of a turbine cylinder body and the turbine efficiency are also reduced, the upper end wall structure of the existing gas generator turbine has more connecting parts, the assembling steps are complex, the consumed time is long, the upper end wall structure of the existing gas generator turbine of a medium and small-sized gas turbine is not perfect, and the technology is not mature.
Therefore, it is desirable to provide an upper end wall structure of a gas generator turbine suitable for small and medium-sized combustion engines to solve the above technical problems.
SUMMERY OF THE UTILITY MODEL
The present invention has been developed in order to solve the problems of sealing and upper endwall compact attachment of the mainstream gas passage of a gas turbine, and a brief summary of the invention is provided below in order to provide a basic understanding of certain aspects of the invention. It should be understood that this summary is not an exhaustive overview of the invention. It is not intended to identify key or critical elements of the invention or to delineate the scope of the invention.
The technical scheme of the utility model:
the utility model provides a gas generator turbine upper end wall structure suitable for little combustion engine, including first order stationary blade, the turbine cylinder body, first order moving blade, the moving blade retaining ring, the moving blade is held the ring, long ring, second level stationary blade, second level moving blade, first order stationary blade is connected the installation with the turbine cylinder body, the moving blade is held the ring and is connected the installation with the turbine cylinder body, the moving blade retaining ring is installed on the moving blade retaining ring, first honeycomb seal structure has been arranged between moving blade retaining ring and the first order moving blade, first honeycomb seal structure installs on the moving blade retaining ring, long holding ring fixed mounting is on the turbine cylinder body, second level blade passes through bolt fixed mounting on long holding the ring, be provided with second honeycomb seal structure on the second level stationary blade, second level moving blade is arranged and is being in second honeycomb seal structure looks adaptation.
Preferably: the first stage of the turbine engine comprises a turbine cylinder body, a first stage of stationary blades and a second stage of stationary blades, wherein the first stage of the turbine cylinder body is provided with a first groove, and the first groove is formed in the first stage of the turbine cylinder body.
Preferably: and a second bulge is processed on the movable blade holding ring, a second groove is processed on the turbine cylinder body, and the second bulge on the movable blade holding ring is arranged in the second groove on the turbine cylinder body.
Preferably: and a third bulge is processed on the movable blade retaining ring, a third groove is processed on the movable blade holding ring, and the third bulge on the movable blade retaining ring is arranged in the third groove on the movable blade holding ring.
Preferably: and a fourth bulge is processed on the second-stage stationary blade, a fourth groove is processed on the long holding ring, and the fourth bulge on the second-stage stationary blade is arranged in the fourth groove on the long holding ring. The utility model discloses a when solving handheld calabash silk of player and sitting down, the bamboo pipe of calabash silk and the desktop in player the place ahead bump's problem is proposed the technical scheme of the utility model is:
the utility model discloses following beneficial effect has:
1. the first-stage stationary blade and the second-stage stationary blade of the utility model are directly connected with the turbine cylinder body, so that the number of connecting pieces is reduced, the structure is compact and simple, the assembly difficulty is reduced, and the working efficiency is improved;
2. the honeycomb sealing structure is arranged at the top of the first-stage movable vane, the clearance is reduced, the pneumatic efficiency is improved, and meanwhile, the movable vane retaining ring is convenient to replace and maintain;
3. the second-stage moving blade end wall of the utility model is adaptive to the flow field design, improves the pneumatic efficiency, and has a honeycomb sealing structure at the top, further improves the pneumatic efficiency by reducing the clearance, thereby effectively improving the service life of the turbine cylinder body and the turbine efficiency;
4. the utility model discloses a gas generator turbine upper end wall structure suitable for medium and small gas turbine, simple structure, design benefit, easy dismounting, equipment are firm, are suitable for using widely.
Drawings
FIG. 1 is a block diagram of the upper turbine endwall configuration of a gas generator suitable for use in medium and small combustion engines;
FIG. 2 is a schematic view of the upper end wall structure of a gas generator turbine suitable for small and medium-sized combustion engines;
FIG. 3 is a block diagram of the upper end wall structure of the gas generator turbine suitable for small and medium-sized combustion engines;
in the figure, 1-first stage stationary blades, 2-turbine cylinder body, 3-first stage moving blades, 4-moving blade retaining rings, 5-first honeycomb sealing structure, 6-moving blade retaining rings, 7-long retaining rings, 8-second stage stationary blades, 9-second honeycomb sealing structure, 10-second stage moving blades, 1-1-first protrusions, 2-1-first grooves, 2-2-second grooves, 4-1-third protrusions, 6-1-second protrusions, 6-2-third grooves, 7-1-fourth grooves and 8-1-fourth protrusions.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described below with reference to specific embodiments shown in the accompanying drawings. It should be understood that the description is intended to be illustrative only and is not intended to limit the scope of the present invention. Moreover, in the following description, descriptions of well-known structures and techniques are omitted so as to not unnecessarily obscure the concepts of the present invention.
The utility model discloses the connection that mentions divide into fixed connection and can dismantle the connection, fixed connection is for the conventional fixed connection mode such as undetachable connection including but not limited to hem connection, rivet connection, adhesive connection and welded connection, can dismantle the connection including but not limited to conventional dismantlement modes such as threaded connection, buckle connection, pin joint and hinged joint, when not clearly prescribing a limit to concrete connection mode, acquiesces to always can find at least one kind of connected mode in current connected mode and can realize this function, and the technical staff in the art can select by oneself as required. For example: the fixed connection selects welding connection, and the detachable connection selects hinge connection.
The first embodiment is as follows: the present embodiment is described with reference to fig. 1 to 3, and the upper end wall structure of a gas generator turbine suitable for a medium-small combustion engine of the present embodiment includes a first stage stationary blade 1, a turbine cylinder 2, a first stage moving blade 3, a moving blade retaining ring 4, a moving blade retaining ring 6, a long retaining ring 7, a second stage stationary blade 8, and a second stage moving blade 10, wherein the first stage stationary blade 1 is connected to the turbine cylinder 2, the moving blade retaining ring 6 is connected to the turbine cylinder 2, the moving blade retaining ring 4 is mounted to the moving blade retaining ring 6, a first honeycomb seal structure 5 is disposed between the moving blade retaining ring 4 and the first stage moving blade 3, the first honeycomb seal structure 5 is mounted to the moving blade retaining ring 4, the long retaining ring 7 is fixedly mounted to the turbine cylinder 2, the second stage stationary blade 8 is fixedly mounted to the long retaining ring 7 by a bolt, a second honeycomb seal structure 9 is disposed on the second stage stationary blade 8, the second-stage moving blades 10 are arranged to be matched with the second honeycomb sealing structure 9, the moving blade retaining ring 4, the moving blade retaining ring 6 and the long retaining ring 7 effectively prevent high-temperature gas from transferring heat to a turbine cylinder body, the top shroud of the first-stage moving blades 3 adopts a 3-tooth structure, the top leakage amount of the gas is further reduced, the second-stage stationary blades 8 adopt a long end wall design, the number of parts is reduced, and the first-stage stationary blades 1, the first-stage moving blades 3, the second-stage stationary blades 8 and the second-stage moving blades 10 are arranged in a staggered mode;
the second embodiment is as follows: the embodiment is described with reference to fig. 1 to 3, and the upper end wall structure of the gas generator turbine suitable for a medium-small combustion engine of the embodiment is provided with a first honeycomb sealing structure 5 on the movable blade retaining ring 4, a second honeycomb sealing structure 9 on the second stage stationary blade 8, the first honeycomb sealing structure 5 between the movable blade retaining ring 4 and the first stage moving blade 3 and the second honeycomb sealing structure 9 on the top of the first stage moving blade 3 can reduce the gap and increase the efficiency during operation, and at the same time, the first honeycomb sealing structure 5 and the second honeycomb sealing structure 9 are respectively fixed on the movable blade retaining ring 4 and the second stage stationary blade 8, so that the replacement is particularly convenient during actual unit maintenance, and the second honeycomb sealing structure 9 is arranged in a stepped structure to reduce the leakage amount of the movable blade top and improve the pneumatic efficiency.
The third concrete implementation mode: the embodiment is described with reference to fig. 1 to 3, and the upper end wall structure of the gas generator turbine suitable for the medium and small combustion engines of the embodiment is characterized in that a first protrusion 1-1 is machined on the first-stage stationary blade 1, a first groove 2-1 is machined on the turbine cylinder body 2, and the first protrusion 1-1 on the first-stage stationary blade 1 is installed in the first groove 2-1 on the turbine cylinder body 2.
The fourth concrete implementation mode: the embodiment is described with reference to fig. 1 to 3, and the upper end wall structure of the gas generator turbine suitable for the medium and small combustion engine of the embodiment is that the second protrusion 6-1 is processed on the movable blade holding ring 6, the second groove 2-2 is processed on the turbine cylinder 2, the second protrusion 6-1 on the movable blade holding ring 6 is installed in the second groove 2-2 on the turbine cylinder 2, and the movable blade holding ring 6 is used as a connecting carrier of the turbine cylinder 2 and the movable blade guard ring 4, and the material requirement in practical application is relatively low.
The fifth concrete implementation mode: the present embodiment will be described with reference to fig. 1 to 3, and the present embodiment is a top wall structure of a gas generator turbine suitable for a medium or small combustion engine, in which a third protrusion 4-1 is formed on the moving blade retaining ring 4, a third groove 6-2 is formed on the moving blade retaining ring 6, and the third protrusion 4-1 on the moving blade retaining ring 4 is fitted into the third groove 6-2 on the moving blade retaining ring 6.
The sixth specific implementation mode: the embodiment is described with reference to fig. 1 to 3, and the upper end wall structure of the gas generator turbine suitable for the medium and small combustion engines of the embodiment is characterized in that fourth protrusions 8-1 are machined on the second-stage stationary blades 8, fourth grooves 7-1 are machined on the long supporting ring 7, the fourth protrusions 8-1 on the second-stage stationary blades 8 are installed in the fourth grooves 7-1 on the long supporting ring 7, and the long supporting ring 7 can play a role in distributing the flow of cold air.
It should be noted that, in the above embodiments, as long as the technical solutions can be aligned and combined without contradiction, those skilled in the art can exhaust all possibilities according to the mathematical knowledge of the alignment and combination, and therefore the present invention does not describe the technical solutions after alignment and combination one by one, but it should be understood that the technical solutions after alignment and combination have been disclosed by the present invention.
This embodiment is only illustrative of the patent and does not limit the scope of protection thereof, and those skilled in the art can make modifications to its part without departing from the spirit of the patent.
Claims (5)
1. A gas generator turbine upper end wall structure suitable for medium and small combustion engines is characterized in that: comprises a first-stage stationary blade (1), a turbine cylinder body (2), a first-stage moving blade (3), a moving blade retaining ring (4), a moving blade retaining ring (6), a long retaining ring (7), a second-stage stationary blade (8) and a second-stage moving blade (10), wherein the first-stage stationary blade (1) is connected with the turbine cylinder body (2), the moving blade retaining ring (6) is connected with the turbine cylinder body (2), the moving blade retaining ring (4) is arranged on the moving blade retaining ring (6), a first honeycomb sealing structure (5) is arranged between the moving blade retaining ring (4) and the first-stage moving blade (3), the first honeycomb sealing structure (5) is arranged on the moving blade retaining ring (4), the long retaining ring (7) is fixedly arranged on the turbine cylinder body (2), the second-stage stationary blade (8) is fixedly arranged on the long retaining ring (7) through a bolt, and a second honeycomb sealing structure (9) is arranged on the second-stage stationary blade (8), the second stage moving blades (10) are arranged to fit the second honeycomb seal structure (9).
2. The upper end wall structure of a gas generator turbine suitable for a medium-small combustion engine as claimed in claim 1, wherein: a first bulge (1-1) is machined on the first-stage stationary blade (1), a first groove (2-1) is machined on the turbine cylinder body (2), and the first bulge (1-1) on the first-stage stationary blade (1) is installed in the first groove (2-1) on the turbine cylinder body (2).
3. The upper end wall structure of a gas generator turbine suitable for a medium-small combustion engine as claimed in claim 1, wherein: the second bulge (6-1) is machined on the movable blade holding ring (6), the second groove (2-2) is machined on the turbine cylinder body (2), and the second bulge (6-1) on the movable blade holding ring (6) is installed in the second groove (2-2) on the turbine cylinder body (2).
4. The upper end wall structure of a gas generator turbine suitable for a medium-small combustion engine as claimed in claim 1, wherein: the movable blade protective ring (4) is provided with a third bulge (4-1), the movable blade holding ring (6) is provided with a third groove (6-2), and the third bulge (4-1) on the movable blade protective ring (4) is arranged in the third groove (6-2) on the movable blade holding ring (6).
5. The upper end wall structure of a gas generator turbine suitable for a medium-small combustion engine as claimed in claim 1, wherein: fourth protrusions (8-1) are machined on the second-stage stationary blades (8), fourth grooves (7-1) are machined on the long holding ring (7), and the fourth protrusions (8-1) on the second-stage stationary blades (8) are installed in the fourth grooves (7-1) on the long holding ring (7).
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| Application Number | Priority Date | Filing Date | Title |
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| CN202021097787.5U CN212177222U (en) | 2020-06-15 | 2020-06-15 | Gas generator turbine upper end wall structure suitable for medium and small gas turbines |
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| CN202021097787.5U CN212177222U (en) | 2020-06-15 | 2020-06-15 | Gas generator turbine upper end wall structure suitable for medium and small gas turbines |
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| CN212177222U true CN212177222U (en) | 2020-12-18 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112879163A (en) * | 2021-01-11 | 2021-06-01 | 哈电发电设备国家工程研究中心有限公司 | Novel air flow distribution conversion device for air circuit conversion |
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2020
- 2020-06-15 CN CN202021097787.5U patent/CN212177222U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112879163A (en) * | 2021-01-11 | 2021-06-01 | 哈电发电设备国家工程研究中心有限公司 | Novel air flow distribution conversion device for air circuit conversion |
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