CN112943389A - Engine turbine shell structure - Google Patents
Engine turbine shell structure Download PDFInfo
- Publication number
- CN112943389A CN112943389A CN202110117266.4A CN202110117266A CN112943389A CN 112943389 A CN112943389 A CN 112943389A CN 202110117266 A CN202110117266 A CN 202110117266A CN 112943389 A CN112943389 A CN 112943389A
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- Prior art keywords
- turbine
- turbine shell
- channel
- temperature gas
- shell
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000001816 cooling Methods 0.000 claims abstract description 17
- 239000002826 coolant Substances 0.000 claims description 60
- 230000000149 penetrating effect Effects 0.000 claims description 5
- 230000003014 reinforcing effect Effects 0.000 claims description 4
- 239000011257 shell material Substances 0.000 description 55
- 239000007789 gas Substances 0.000 description 45
- 238000000034 method Methods 0.000 description 3
- 239000000567 combustion gas Substances 0.000 description 2
- 238000004891 communication Methods 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Images
Classifications
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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
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
-
- 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
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
-
- 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
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/14—Casings modified therefor
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to the technical field of rotating machinery, and provides a turbine shell structure of an engine, which can ensure that high-temperature gas smoothly passes through, a bearing stably runs and the pressure in an inner cavity of the turbine shell is effectively adjusted, so that a turbine rotor safely works; the gas channel comprises a high-temperature gas channel which is integrally formed on the outer side wall of the turbine shell and extends into the turbine shell, two ends of the high-temperature gas channel are respectively connected with a high-temperature gas inlet and a high-temperature gas outlet, and the high-temperature gas outlet is formed in the inner wall of the turbine side shell. The turbine shell body has the advantages that the functions of diversion, cooling, pressure balancing and the like of the turbine shell body are integrated, and the turbine shell body has higher social use value and application prospect.
Description
Technical Field
The invention relates to the technical field of rotating machinery, in particular to a turbine shell structure of an engine.
Background
The turbine shell is an outer shell wrapping the turbine disc and used for guiding high-temperature gas to enter the turbine so that the turbine disc rotates at a high speed and the purpose of power input is achieved. Generally, the temperature of the turbine gas used on the engine can reach over 1200K, and through the heat conduction of the shell material, the temperature of the bearing mounting seat in the inner cavity of the turbine shell even exceeds the service temperature of a conventional bearing, so that the high-temperature failure of the bearing is caused. In addition, the high-temperature combustion gas often has very high pressure, so that the axial force applied to the turbine rotor and the bearing is not matched, and the bearing is damaged in an overload mode.
In the prior art, turbine casing structures generally only satisfy axial flow turbine designs or only satisfy partial intake designs, with the following disadvantages:
1. the turbine design adopting local air intake can enable the turbine shell structure to be more compact and lighter, and the turbine shell structure is generally applied under low flow, but the lack of cooling design can cause the temperature of the bearing to exceed the application range, and the bearing cannot normally run;
2. the lack of a pressure balance design may cause the axial force borne by the bearing to exceed the use range of the bearing, the bearing cannot normally run, and high-temperature gas passes through the turbine shell, so that the temperature of the turbine shell is inevitably increased and often exceeds the use environment temperature of the bearing;
3. in addition, the passage of high temperature combustion gases may also cause the pressure in the inner cavity of the turbine housing to rise, possibly causing the axial force applied to the bearing to exceed the application range. A turbine shell which is specially designed to meet the functions of diversion, cooling, pressure balancing and the like is not provided, and therefore an engine turbine shell structure is provided.
Disclosure of Invention
Technical problem to be solved
Aiming at the defects of the prior art, the invention provides the turbine shell structure of the engine, which overcomes the defects of the prior art, has reasonable design and compact structure, and can ensure that high-temperature gas smoothly passes through, a bearing stably runs and the pressure in the inner cavity of the turbine shell is effectively adjusted, thereby realizing the safe work of a turbine rotor and improving the reliability of the engine.
(II) technical scheme
In order to achieve the purpose, the invention is realized by the following technical scheme:
a turbine shell structure of an engine comprises a turbine side shell, a press side shell, a bearing mounting seat for connecting the turbine side shell and the press side shell, a gas channel, a cooling channel and a pressure balance channel, wherein the gas channel, the cooling channel and the pressure balance channel are arranged in the turbine shell and do not interfere with each other;
the gas channel comprises a high-temperature gas channel which is integrally formed on the outer side wall of the turbine shell and extends into the turbine shell, two ends of the high-temperature gas channel are respectively connected with a high-temperature gas inlet and a high-temperature gas outlet, and the high-temperature gas outlet is formed in the inner wall of the turbine side shell;
the cooling channel comprises a plurality of cooling agent distribution pipes which are integrally formed in the turbine shell and are in an arc shape, two ends of each cooling agent distribution pipe are respectively connected with an inlet of each cooling agent distribution pipe and an outlet of each cooling agent distribution pipe, the inlets of the cooling agent distribution pipes are connected with cooling agent inlets located on the outer side wall of the turbine shell in a penetrating manner, and the outlets of the cooling agent distribution pipes are connected with cooling agent outlets located on the outer side wall of the turbine shell in a penetrating manner;
the pressure balance channel comprises an L-shaped pressure balance channel which is integrally formed inside the turbine shell, two ends of the pressure balance channel are respectively connected to a pressure balance hole inlet and a pressure balance hole outlet, the pressure balance hole inlet is formed in the inner wall of the turbine side shell, and the pressure balance hole outlet is formed in the outer side wall of the turbine shell.
Preferably, the coolant outlet comprises a first arcuate channel communicating with the coolant distribution pipe outlet and a first cylindrical channel connected through the other end of the first arcuate channel.
Preferably, the coolant inlet comprises a second arcuate channel in communication with the coolant distribution pipe inlet and a second cylindrical channel in communication with the other end of the second arcuate channel.
Preferably, the cross section of the high-temperature gas inlet is circular, the cross section of the high-temperature gas outlet is in the shape of a ring sector, and the cross section of the high-temperature gas flow channel is in the shape of a circular arc.
Preferably, the pressure balance hole outlet is arranged in a direction perpendicular to the central axis of the turbine housing and connected with the external interface.
Preferably, a plurality of the coolant distribution pipes are uniformly arranged along a circumferential direction of the bearing mount.
Preferably, the coolant inlet and the coolant outlet are located adjacent to one end of the outer sidewall of the turbine housing.
Preferably, the annular side wall of the shell structure is provided with reinforcing ribs uniformly arranged along the circumferential direction of the turbine shell.
(III) advantageous effects
The embodiment of the invention provides an engine turbine shell structure, which has the following beneficial effects:
1. the invention can ensure that high-temperature gas smoothly passes through, the bearing stably runs and the pressure in the inner cavity of the turbine shell is effectively adjusted, thereby realizing the safe work of the turbine rotor and improving the reliability of the engine.
2. The invention carries out ingenious cooling flow channel design around the bearing mounting seat, and simultaneously avoids the cooling flow channel and the pressure balance flow channel, thereby leading the structure to be more compact and effectively reducing the structural weight.
3. The turbine housing integrates three functions of gas diversion, cooling and pressure balancing, high-temperature gas can enter the turbine housing through the gas flow passage, a coolant can cool the bearing mounting seat of the turbine housing, and the pressure balancing hole can adjust the pressure in the inner cavity of the turbine housing, so that the axial force of the bearing is adjusted, the effective operation of a turbine rotor is ensured, and the functions of diversion, cooling, pressure balancing and the like of the turbine housing are integrated.
Drawings
The above features, technical features, advantages and modes of realisation of a turbine shell structure for an engine will be further described in the following, in a clearly understandable manner, with reference to the accompanying drawings, which illustrate preferred embodiments.
FIG. 1 is a schematic view of the present invention;
FIG. 2 is a schematic view of the internal structure of the present invention;
FIG. 3 is a schematic view showing the internal structure of a cooling passage according to the present invention;
fig. 4 is a schematic view of the internal structure of the pressure equalizing hole according to the present invention.
In the figure: the high-temperature gas distribution device comprises a high-temperature gas inlet 1, a high-temperature gas outlet 2, a bearing mounting seat 3, a coolant distribution pipe 4, a coolant inlet 5, a coolant outlet 6, a first arched channel 7, a high-temperature gas flow channel 8, a first cylindrical channel 9, a coolant distribution pipe outlet 10, a coolant distribution pipe inlet 11, a second arched channel 12, a second cylindrical channel 13, a pressure balance hole inlet 14, a pressure balance channel 15, a pressure balance hole outlet 16 and reinforcing ribs 17.
Detailed Description
The invention will be further illustrated with reference to the following figures 1-4 and examples:
example 1
A turbine shell structure of an engine comprises a turbine side shell, a press side shell, a bearing mounting seat 3 for connecting the turbine side shell and the press side shell, a gas channel, a cooling channel and a pressure balance channel, wherein the gas channel, the cooling channel and the pressure balance channel are arranged in the turbine shell and do not interfere with each other;
the gas channel comprises a high-temperature gas flow channel 8 which is integrally formed on the outer side wall of the turbine shell and extends into the turbine shell, two ends of the high-temperature gas flow channel 8 are respectively connected with a high-temperature gas inlet 1 and a high-temperature gas outlet 2, and the high-temperature gas outlet 2 is arranged on the inner wall of the turbine shell;
the cooling channel comprises a plurality of cooling agent distribution pipes 4 which are integrally formed in the turbine shell and are in the shape of an arc, wherein the cross section of a flow channel of each cooling agent distribution pipe 4 is in the shape of an arc, so that the cooling agent distribution pipes are wrapped on bearing seats, and the inlet and the outlet of the cooling agent are not interfered with each other, the two ends of each cooling agent distribution pipe 4 are respectively connected to a cooling agent distribution pipe inlet 11 and a cooling agent distribution pipe outlet 10, the cooling agent distribution pipe inlets 11 are connected with cooling agent inlets 5 located on the outer side wall of the turbine shell in a penetrating manner, and the cooling agent distribution pipe outlets 10 are connected with cooling agent outlets 6 located;
the pressure balance channel comprises an L-shaped pressure balance flow channel 15 which is integrally formed in the turbine shell, two ends of the pressure balance flow channel 15 are respectively connected with a pressure balance hole inlet 14 and a pressure balance hole outlet 16, the pressure balance hole inlet 14 is formed in the inner wall of the turbine side shell, and the pressure balance hole outlet 16 is formed in the outer side wall of the turbine shell; it will be appreciated that the L-shaped bend location of the pressure balance channel 15 reduces flow resistance by an annular smooth transition.
The coolant outlet 6 comprises a first arched channel 7 communicated with a coolant distribution pipe outlet 10 and a first cylindrical channel 9 communicated with the other end of the first arched channel 7; the coolant inlet 5 comprises a second arched channel 12 communicated with the coolant distribution pipe inlet 11 and a second cylindrical channel 13 communicated with the other end of the second arched channel 12;
in the embodiment, high-temperature gas enters the high-temperature gas flow channel 8 through the high-temperature gas inlet 1 and is discharged from the high-temperature gas outlet 2, so that the temperature of the turbine shell is increased in the process, and the temperature of a bearing arranged in the turbine shell is also increased;
the coolant enters the coolant distribution pipe 4 through the coolant inlet 5 and is discharged through the coolant outlet 6, the ambient temperature at the bearing mounting seat 3 is greatly reduced in the process, the temperature of the bearing mounted in the turbine shell is reduced, and the normal operation of the bearing is ensured;
high-pressure gas in the turbine shell enters a pressure balance flow channel 15 through a pressure balance hole inlet 14 and is discharged from a pressure balance hole outlet 16, the pressure of the inner cavity of the turbine shell can be adjusted in the process, and the axial force borne by the bearing is ensured to meet the requirement;
thereby satisfied functions such as the water conservancy diversion of turbine housing, cooling, balanced pressure in an organic whole, ensured that high temperature gas passes through smoothly, the stable operation of bearing and the effective regulation of turbine housing inner chamber pressure, realized turbine rotor safety work, improved engine's reliability.
Example 2
The difference between the present embodiment and embodiment 1 is that, as shown in fig. 1-3, the cross section of the high-temperature gas inlet 1 is circular, the cross section of the high-temperature gas outlet 2 is ring sector, and the cross section of the high-temperature gas flow channel 8 is circular arc;
in this embodiment, the high temperature gas runner 8 is arc-shaped, and can reduce the choked flow, and the cross-section of high temperature gas export 2 is ring sector, and the high temperature gas blows to the turbine dish in the turbine casing through high temperature gas export 2, makes the turbine dish rotate at a high speed, reaches power input's purpose, also can guarantee the evenly distributed of high temperature gas in the turbine casing simultaneously.
Example 3
The present embodiment is different from embodiment 1 in that, as shown in fig. 1 and 4, the pressure balance hole outlet 16 is arranged in a direction perpendicular to the turbine housing central axis and meets the external interface;
in this embodiment, the vertical arrangement of the pressure balance hole outlet 16 facilitates installation of the test device.
Example 2
The present embodiment differs from embodiment 1 in that, as shown in fig. 2 and 4, a plurality of the coolant distribution pipes 4 are uniformly arranged along the circumferential direction of the bearing mount 3;
in this embodiment, the plurality of coolant distribution pipes 4 can maximally cool the bearing temperature at the turbine housing and the bearing mount 3.
Example 2
This embodiment differs from embodiment 1 in that, as shown in fig. 3, the coolant inlet 5 and the coolant outlet 6 are disposed adjacent to each other at one end of the outer side wall of the turbine housing;
in this embodiment, the provision of the coolant inlet 5 and the coolant outlet 6 allows the turbine housing to be cooled to the maximum extent, ensuring that the bearings operate properly.
Example 2
The difference between the present embodiment and embodiment 1 is that, as shown in fig. 1, the annular side wall of the casing structure is provided with reinforcing ribs 17 uniformly arranged along the circumferential direction of the turbine casing;
in this embodiment, the design of strengthening rib 17 can guarantee turbine shell structural strength, can alleviate turbine shell weight again.
Other undescribed structures refer to example 1.
The embodiments of the present invention are disclosed as the preferred embodiments, but not limited thereto, and those skilled in the art can easily understand the spirit of the present invention and make various extensions and changes without departing from the spirit of the present invention.
Claims (8)
1. The turbine shell structure of the engine is characterized in that the turbine shell consists of a turbine side shell, a press side shell and a bearing mounting seat (3) for connecting the turbine side shell and the press side shell, and also comprises a gas channel, a cooling channel and a pressure balance channel which are arranged in the turbine shell and do not interfere with each other;
the gas channel comprises a high-temperature gas channel (8) which is integrally formed on the outer side wall of the turbine shell and extends into the turbine shell, two ends of the high-temperature gas channel (8) are respectively connected with a high-temperature gas inlet (1) and a high-temperature gas outlet (2), and the high-temperature gas outlet (2) is formed in the inner wall of the turbine side shell;
the cooling channel comprises a plurality of cooling agent distribution pipes (4) which are integrally formed in the turbine shell and are in the shape of circular arcs, two ends of each cooling agent distribution pipe (4) are respectively connected to an inlet (11) and an outlet (10) of each cooling agent distribution pipe, the inlets (11) of the cooling agent distribution pipes are connected with cooling agent inlets (5) located on the outer side wall of the turbine shell in a penetrating manner, and the outlets (10) of the cooling agent distribution pipes are connected with cooling agent outlets (6) located on the outer side wall of the turbine shell in a penetrating manner;
the pressure balance channel comprises a pressure balance channel (15) which is integrally formed inside the turbine shell and is L-shaped, two ends of the pressure balance channel (15) are respectively connected to a pressure balance hole inlet (14) and a pressure balance hole outlet (16), the pressure balance hole inlet (14) is formed in the inner wall of the turbine side shell, and the pressure balance hole outlet (16) is formed in the outer side wall of the turbine shell.
2. An engine turbine shell structure according to claim 1, wherein: the coolant outlet (6) comprises a first arched channel (7) communicated with the coolant distribution pipe outlet (10) and a first cylindrical channel (9) communicated with the other end of the first arched channel (7).
3. An engine turbine shell structure according to claim 1, wherein: the coolant inlet (5) comprises a second arched channel (12) communicated with the coolant distribution pipe inlet (11) and a second cylindrical channel (13) communicated with the other end of the second arched channel (12).
4. An engine turbine shell structure according to claim 1, wherein: the section of the high-temperature gas inlet (1) is circular, the section of the high-temperature gas outlet (2) is in the shape of a ring sector, and the section of the high-temperature gas flow channel (8) is in the shape of a circular arc.
5. An engine turbine shell structure according to claim 1, wherein: the pressure balance hole outlet (16) is arranged in a direction perpendicular to the central axis of the turbine shell and is connected with an external interface.
6. An engine turbine shell structure according to claim 1, wherein: the coolant distribution pipes (4) are uniformly arranged along the circumferential direction of the bearing mounting seat (3).
7. An engine turbine shell structure according to claim 1, wherein: the coolant inlet (5) and the coolant outlet (6) are arranged adjacently at one end of the outer side wall of the turbine housing.
8. An engine turbine shell structure according to claim 1, wherein: and reinforcing ribs (17) uniformly arranged along the circumferential direction of the turbine shell are arranged on the annular side wall of the shell structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110117266.4A CN112943389A (en) | 2021-01-28 | 2021-01-28 | Engine turbine shell structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110117266.4A CN112943389A (en) | 2021-01-28 | 2021-01-28 | Engine turbine shell structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112943389A true CN112943389A (en) | 2021-06-11 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110117266.4A Pending CN112943389A (en) | 2021-01-28 | 2021-01-28 | Engine turbine shell structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112943389A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100183439A1 (en) * | 2009-01-22 | 2010-07-22 | General Electric Company | Systems, Methods, and Apparatus for Controlling Gas Leakage in a Turbine |
| CN205936713U (en) * | 2016-08-25 | 2017-02-08 | 南通市嘉诚机械有限公司 | Turbocharger bearing casing |
| CN108979844A (en) * | 2018-09-07 | 2018-12-11 | 厦门锡恩重卡科技有限公司 | Turbo charging installation and its application method |
| CN111765114A (en) * | 2020-06-17 | 2020-10-13 | 新乡航空工业(集团)有限公司 | Axial force balance structure of boosting type air-floating turbine cooler |
-
2021
- 2021-01-28 CN CN202110117266.4A patent/CN112943389A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100183439A1 (en) * | 2009-01-22 | 2010-07-22 | General Electric Company | Systems, Methods, and Apparatus for Controlling Gas Leakage in a Turbine |
| CN205936713U (en) * | 2016-08-25 | 2017-02-08 | 南通市嘉诚机械有限公司 | Turbocharger bearing casing |
| CN108979844A (en) * | 2018-09-07 | 2018-12-11 | 厦门锡恩重卡科技有限公司 | Turbo charging installation and its application method |
| CN111765114A (en) * | 2020-06-17 | 2020-10-13 | 新乡航空工业(集团)有限公司 | Axial force balance structure of boosting type air-floating turbine cooler |
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Application publication date: 20210611 |