CN114087072A - Gas turbine and gas turbine with same - Google Patents
Gas turbine and gas turbine with same Download PDFInfo
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- CN114087072A CN114087072A CN202111201203.3A CN202111201203A CN114087072A CN 114087072 A CN114087072 A CN 114087072A CN 202111201203 A CN202111201203 A CN 202111201203A CN 114087072 A CN114087072 A CN 114087072A
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- cold air
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- pressure chamber
- seal groove
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- 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
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
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- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a gas turbine and a gas turbine with the same, wherein the gas turbine comprises: the sealing device comprises a body, a first separating part, a first sealing sheet and a second sealing sheet; the body has gas channel and air conditioning chamber, the air conditioning chamber includes high pressure chamber and low pressure chamber, high pressure chamber and low pressure chamber are spaced apart in the axial of body, form gas channel between body and the first partition portion, first partition portion has the air conditioning chamber, first partition portion still has first air conditioning passageway and second air conditioning passageway, each in high pressure chamber and the low pressure chamber passes through first air conditioning passageway and gas channel intercommunication, the low pressure chamber still passes through second air conditioning passageway and gas channel intercommunication, first gasket is established in first air conditioning passageway, the second gasket is established in first air conditioning passageway, have the gap with high pressure chamber intercommunication between first gasket and the second gasket. The gas turbine of the present invention has the advantage of high cooling efficiency.
Description
Technical Field
The invention relates to the technical field of gas turbines, in particular to a gas turbine and a gas turbine with the same.
Background
The gas turbine is an internal combustion type power machine which takes continuously flowing gas as a working medium to drive an impeller to rotate at a high speed so as to convert the energy of fuel into mechanical energy, wherein the turbine is one of core components of the gas turbine. When the turbine is operated in a high temperature environment, it is necessary to prevent high temperature gas from intruding into the non-flow path surface from the gap between the lower edge plate of the moving blade and the lower edge plate of the stationary blade of the turbine. In the related art, the cool air leaks into the gas passage through the cool air cavities inside the lower edge plates of the moving blades and the lower edge plates of the stationary blades, thereby preventing the invasion of high-temperature gas.
Disclosure of Invention
The present invention is based on the discovery and recognition by the inventors of the following facts and problems:
in the related art gas turbine, cool air leaks into the gas passage through a cool air chamber inside the lower edge plates of the moving blades and the lower edge plates of the stationary blades, thereby preventing the intrusion of high-temperature gas. Wherein the air conditioning chamber includes high-pressure chamber and low pressure chamber, and high-pressure chamber and low pressure chamber all leak the air conditioning to the circumferential clearance of stator blade lower limb, and then avoid high temperature gas to invade non-runner face from the circumferential clearance of stator blade lower limb to the low pressure chamber still need leak the air conditioning to the axial clearance between rotor blade lower limb and the stator blade lower limb, and then avoid the high temperature gas to invade non-runner face from the circumferential clearance of rotor blade lower limb and stator blade lower limb.
However, since the high-temperature gas pressure at the circumferential gap between the lower edge plates of the stationary blades is higher than the high-temperature gas pressure at the axial gap between the lower edge plates of the moving blades and the lower edge plates of the stationary blades, and the pressure difference is large, and further, the cold air pressure in the low-pressure chamber needs to be higher than the high-temperature gas pressure at the circumferential gap between the lower edge plates of the stationary blades, so that the invasion of the high-temperature gas can be avoided, the pressure difference between the cold air pressure in the low-pressure chamber and the high-temperature gas pressure at the axial gap between the lower edge plates of the moving blades and the lower edge plates of the stationary blades is large, so that a large amount of cooling gas leaks from the axial gap between the lower edge plates of the driven blades and the lower edge plates of the stationary blades in the low-pressure chamber, the usage amount of cold air in the gas turbine is increased, and the cooling efficiency of the gas turbine is reduced.
The present invention is directed to solving, at least to some extent, one of the technical problems in the related art. To this end, embodiments of the present invention provide a gas turbine that has the advantage of high cooling efficiency.
Embodiments of the present invention also provide a gas turbine having a gas turbine with the advantage of high cooling efficiency.
A gas turbine according to an embodiment of the present invention includes: a body having a gas passage and a cold gas cavity comprising a high pressure cavity and a low pressure cavity, the high pressure cavity and the low pressure cavity being spaced apart in an axial direction of the body; the body is provided with a peripheral wall which is sleeved on the first partition part, the gas channel is formed between the peripheral wall and the first partition part, the first partition part is provided with the cold air cavity, the first partition part is provided with a cold air inlet communicated with the high pressure cavity, the cold air inlet is used for being communicated with a cold air source, the first partition part is further provided with a first cold air channel and a second cold air channel, the first cold air channel is provided with a first side wall and a second side wall, each of the high pressure cavity and the low pressure cavity is communicated with the gas channel through the first cold air channel, and the low pressure cavity is further communicated with the gas channel through the second cold air channel; the first sealing sheet is arranged in the first cold air channel to block the gas channel from the high-pressure cavity and the gas channel from the low-pressure cavity, and a ventilation gap is formed between the first sealing sheet and the first side wall and between the first sealing sheet and the second side wall; the second gasket, the second gasket is established in the first air conditioning passageway, in order to the separation the gas passageway with the low pressure chamber, first gasket with have between the second gasket with the gap of high pressure chamber intercommunication, the second gasket with first lateral wall with air permeable gap has between the second lateral wall.
According to the embodiment of the invention, a gap communicated with the high-pressure cavity is formed between the first sealing sheet and the second sealing sheet of the gas turbine, cold air in the high-pressure cavity can enter between the first sealing sheet and the second sealing sheet, the pressure of cold air in the gap is consistent with that of the cold air in the high-pressure cavity, and the pressure of the cold air in the high-pressure cavity is greater than the maximum value of the pressure of gas in the first cold air channel and the second cold air channel, so that the gas in the gas channel is prevented from entering the low-pressure cavity through the first cold air channel.
In addition, the cold air pressure in the gap between first gasket and the second gasket is greater than the gas pressure in the region that gas channel and first cooling channel correspond, guarantees that the gas in the gas channel can not invade the low-pressure chamber from first cold air channel, and then hinders with the region that first cooling channel corresponds in with the low-pressure chamber and the gas channel and separate. The cold air pressure in the low-pressure cavity only needs to be greater than the gas pressure in the area corresponding to the gas channel and the second cold air channel, so that the gas in the gas channel can be prevented from invading the low-pressure cavity, the pressure difference of the corresponding area of the low-pressure cavity and the gas channel of the second cold air channel is reduced, the leakage amount of the cold air leaked from the second cold air channel is reduced, the use amount of the cold air is reduced, and the cooling efficiency of the gas turbine is improved.
Therefore, the gas turbine of the embodiment of the invention has the advantage of high cooling efficiency.
In some embodiments, the first partition includes a second partition located between the high pressure chamber and the low pressure chamber in an axial direction of the body to partition the high pressure chamber and the low pressure chamber.
In some embodiments, the gas turbine of embodiments of the present invention further includes a third seal fin, the second partition having a third cold gas passage, the third cold gas passage having a third side wall and a fourth side wall, the third seal fin being disposed in the third cold gas passage to block the high pressure chamber and the low pressure chamber, the third seal fin having a gas permeable gap with the third side wall and the fourth side wall.
In some embodiments, the second sealing piece is arranged inside the first sealing piece, one side of the second sealing piece in the axial direction of the body is in contact with the first sealing piece, and the other side of the second sealing piece in the axial direction of the body is spaced from the first sealing piece by a preset distance, so that the gap is wedge-shaped.
In some embodiments, the third cold air passage communicates with the first cold air passage, and an outer side of the third sealing sheet is connected to the other side of the second sealing sheet.
In some embodiments, the first sidewall has a first sealing groove and a second sealing groove, the second sidewall has a third sealing groove and a fourth sealing groove, the first sealing sheet includes a first installation portion and a second installation portion, the first installation portion is established in the first sealing groove, the second installation portion is established in the third sealing groove, the second sealing sheet includes a third installation portion and a fourth installation portion, the third installation portion is established in the second sealing groove, the fourth installation portion is established in the fourth sealing groove, the third sidewall has a fifth sealing groove, the fourth sidewall has a sixth sealing groove, the third sealing sheet includes a fifth installation portion and a sixth installation portion, the fifth installation portion is established in the fifth sealing groove, the sixth installation portion is established in the sixth sealing groove, the first installation portion and the wall surface of the first sealing groove are located between each other, The second installation department with between the wall of third seal groove, the third installation department with between the wall of second seal groove, the fourth installation department with between the wall of fourth seal groove, the fifth installation department with between the wall of fifth seal groove and the sixth installation department with have air permeable gap between the wall of sixth seal groove.
In some embodiments, a gas turbine of an embodiment of the present invention further comprises: a stationary blade group including a plurality of stationary blades provided in the gas passage at intervals in a circumferential direction of the body, the stationary blades including stationary blade lower edge plates, the first cold air passage being formed between two of the stationary blade lower edge plates adjacent in the circumferential direction of the body; and a rotor blade group, the stator blade group and the rotor blade group being arranged at intervals in an axial direction of the body, the rotor blade group including a plurality of rotor blades, the plurality of rotor blades being provided in the gas passage at intervals in a circumferential direction of the body, the rotor blade including a rotor blade lower edge plate, the first partition including the stator blade lower edge plate and the rotor blade lower edge plate, the second cold air passage being formed between the stator blade lower edge plate and the rotor blade lower edge plate.
In some embodiments, the stationary blade further includes a partition plate provided inside the stationary blade lower edge plate, the second partition includes the partition plate, and the third cold air passage is formed between two circumferentially adjacent partition plates of the body.
In some embodiments, the stationary blade further includes a stationary blade body provided with an intake passage communicating the cool air inlet and the cool air source.
A gas turbine according to an embodiment of the present invention includes the gas turbine according to any of the above embodiments.
Drawings
FIG. 1 is a schematic block diagram of a gas turbine according to an embodiment of the present invention.
Fig. 2 is a partially enlarged view of fig. 1.
Fig. 3 is a sectional view taken along line a-a of fig. 2.
Fig. 4 is a sectional view taken along line B-B of fig. 2.
FIG. 5 is a schematic block diagram of a gas turbine according to an embodiment of the present invention.
Reference numerals:
a body 1; a gas channel 11; a cold air chamber 12; a high pressure chamber 121; a low pressure chamber 122; a peripheral wall 13;
a first partition 2; a first cold air passage 21; a first sidewall 211; first seal groove 2111; a second seal groove 2112; a second sidewall 212; a third seal groove 2121; a fourth seal groove 2122; a second cold air passage 22; the second partition portion 23; a third cold air path 231; a third sidewall 2311; a fifth seal groove 23111; a fourth sidewall 2312; a sixth seal groove 23121;
a first seal fin 3; a first mounting portion 31; a second mounting portion 32;
a second seal piece 4; a third mounting portion 41; a fourth mounting portion 42;
a third seal fin 5; a fifth mounting portion 51; a sixth mounting portion 52;
a stationary blade group 6; stationary blades 61; a stationary blade lower edge plate 611; a partition plate 612;
a moving blade group 7; the rotor blade 71; the bucket lower plate 711.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
The gas turbine of the present invention is described below with reference to the accompanying drawings.
As shown in fig. 1 to 5, the gas turbine according to the embodiment of the present invention includes a body 1, a first partition 2, a first seal fin 3, and a second seal fin 4.
As shown in fig. 1, the body 1 has a gas combustion passage 11 and a cold air chamber 12, and the cold air chamber 12 includes a high pressure chamber 121 and a low pressure chamber 122, and the high pressure chamber 121 and the low pressure chamber 122 are spaced in an axial direction (left-right direction in fig. 1) of the body 1.
It should be noted that the gas pressure in the area inside the gas channel 11 corresponding to the low-pressure chamber 122 is smaller than the gas pressure in the area inside the gas channel 11 corresponding to the high-pressure chamber 121, that is, when the high-pressure area inside the gas channel 11 is located on the right side of the low-pressure area inside the gas channel 11, the high-pressure chamber 121 may be located on the right side of the low-pressure chamber 122, and when the high-pressure area inside the gas channel 11 is located on the left side of the low-pressure area inside the gas channel 11, the high-pressure chamber 121 may be located on the left side of the low-pressure chamber 122. Specifically, the high pressure chamber 121 is located to the left of the low pressure chamber 122.
The body 1 is provided with a peripheral wall 13, the peripheral wall 13 is sleeved on the first partition part 2, a gas channel 11 is formed between the peripheral wall 13 and the first partition part 2, the first partition part 2 is provided with a cold air cavity 12, the first partition part 2 is provided with a cold air inlet communicated with the high pressure cavity 121, and the cold air inlet is used for being communicated with a cold air source. That is, the cold air source delivers external cold air into the cold air chamber 12 through the cold air inlet, wherein the cold air can enter the high pressure chamber 121 and the low pressure chamber 122 of the cold air chamber 12, wherein the pressure of the cold air in the high pressure chamber 121 is P1, the pressure of the cold air in the low pressure chamber 122 is P2, and the pressure P1 in the high pressure chamber 121 is greater than the pressure P2 in the low pressure chamber 122.
It will be appreciated that the peripheral wall 13 is the cylinder wall of the turbine cylinder.
The first partition 2 further has a first cold air passage 21 and a second cold air passage 22, the first cold air passage 21 having a first side wall 211 and a second side wall 212, each of the high pressure chamber 121 and the low pressure chamber 122 communicating with the gas combustion passage 11 through the first cold air passage 21, the low pressure chamber 122 further communicating with the gas combustion passage 11 through the second cold air passage 22.
Specifically, the cold air in the high pressure chamber 121 and the cold air in the low pressure chamber 122 can be input into the gas combustion channel 11 through the first cold air channel 21, and the cold air in the low pressure chamber 122 can be input into the gas combustion channel 11 through the second cold air channel 22. The maximum value of the gas pressure in the area of the gas channel 11 corresponding to the low pressure cavity 122 is P3, the maximum value of the gas pressure in the area of the gas channel 11 corresponding to the first cold air channel 21 is P4, and the maximum value P3 of the gas pressure in the area of the gas channel 11 corresponding to the low pressure cavity 122 is smaller than the maximum value P4 of the gas pressure in the area of the gas channel 11 corresponding to the first cold air channel 21. The gas pressure of the area of the gas channel 11 corresponding to the second cold air channel 22 is P5, wherein the gas pressure of the area of the gas channel 11 corresponding to the second cold air channel 22 is P5 smaller than P3, and the cold air pressure P1 in the high pressure cavity 121 is larger than P4.
It can be understood that the gas in the gas channel 11 may intrude into the high pressure chamber 121 and the low pressure chamber 122 from the first cold gas channel 21, and therefore the cold gas pressure in the first cold gas channel 21 needs to be greater than P4 to prevent the gas in the gas channel 11 from intruding into the high pressure chamber 121 and the low pressure chamber 122. Moreover, the gas in the gas channel 11 may intrude into the low pressure chamber 122 from the second cold gas channel 22, so the cold gas pressure in the second cold gas channel 22 needs to be greater than P5 to prevent the gas in the gas channel 11 from intruding into the low pressure chamber 122 from the second cold gas channel 22. The first sealing sheet 3 is disposed in the first cold air channel 21 to block the gas channel 11 and the high pressure chamber 121 and the gas channel 11 and the low pressure chamber 122, and a ventilation gap is formed between the first sealing sheet 3 and the first side wall 211 and the second side wall 212.
The second sealing sheet 4 is arranged in the first cold air channel 21 to block the gas channel 11 and the low pressure cavity 122, a gap communicated with the high pressure cavity 121 is formed between the first sealing sheet 3 and the second sealing sheet 4, and a ventilation gap is formed between the second sealing sheet 4 and the first side wall 211 and the second side wall 212.
That is, as shown in fig. 3, the cold air in the high pressure chamber 121 can leak from the air-permeable gap between the first sealing sheet 3 and the first and second side walls 211 and 212 and the air-permeable gap between the second sealing sheet 4 and the first and second side walls 211 and 212, thereby allowing the cold air to leak from the first cold air passage 21 into the gas combustion passage 11. Further, the cold air in the high-pressure chamber 121 can enter the low-pressure chamber 122 from the air-permeable gap between the second sealing sheet 4 and the first and second side walls 211 and 212.
It can be understood that, as shown in fig. 1, the cold air pressure P1 in the high pressure chamber 121 is greater than P4, that is, the cold air pressure in the high pressure chamber 121 is greater than the maximum value of the gas pressure in the area of the gas channel 11 corresponding to the first cold air channel 21, so that the gas in the gas channel 11 cannot enter the high pressure chamber 121 from the first cold air channel 21. In addition, a gap communicated with the high-pressure cavity 121 is formed between the first sealing sheet 3 and the second sealing sheet 4, so that cold air in the high-pressure cavity 121 can enter between the first sealing sheet 3 and the second sealing sheet 4, and the pressure of cold air in the gap is consistent with that of the cold air in the high-pressure cavity 121, so that the pressure of the cold air in the gap is greater than the maximum value of the gas pressure in the region where the gas channel 11 corresponds to the first cold air channel 21, and the gas in the gas channel 11 is prevented from entering the low-pressure cavity 122 through the first cold air channel 21.
And, the cold air pressure in the gap between first gasket 3 and second gasket 4 is greater than the gas pressure in the gas passageway 11 and the regional gas pressure that corresponds first cooling channel 21, guarantees that the gas in the gas passageway 11 can not invade low-pressure chamber 122 from first cold air passageway 21, and then hinders low-pressure chamber 122 and high-pressure chamber and the regional that corresponds first cooling channel 21 in the gas passageway 11 and separate.
That is, the cold air pressure P1 in the high pressure chamber 121 is greater than the maximum value P4 of the gas pressure in the area where the gas channel 11 corresponds to the first cold air channel 21, the maximum value P4 of the gas pressure in the area where the first cold air channel 21 corresponds to is greater than the maximum value P3 of the gas pressure in the area where the gas channel 11 corresponds to the low pressure chamber 122, the maximum value P3 of the gas pressure in the area where the gas channel 11 corresponds to the low pressure chamber 122 is greater than the cold air pressure P2 of the low pressure chamber 122, and the cold air pressure P2 of the low pressure chamber 122 is greater than the gas pressure P5 in the area where the gas channel 11 corresponds to the second cold air channel 22.
Therefore, the cold air pressure P2 in the low pressure chamber 122 is greater than P5 and less than P3, and the cold air in the low pressure chamber 122 can prevent the fuel gas in the fuel gas channel 11 from invading into the low pressure chamber 122, so as to reduce the pressure difference between the low pressure chamber 122 and the areas corresponding to the fuel gas channel 11 and the second cold air channel 22, thereby reducing the leakage amount of the cold air in the second cold air channel 22 and reducing the usage amount of the cold air.
Therefore, the gas turbine of the embodiment of the invention has the advantage of high cooling efficiency.
In some embodiments, as shown in fig. 1, the first partition 2 includes a second partition 23, and the second partition 23 is located between the high pressure chamber 121 and the low pressure chamber 122 in the axial direction of the body 1 to partition the high pressure chamber 121 and the low pressure chamber 122.
Further, the gas turbine according to the embodiment of the present invention further includes a third seal fin 5, the second partition 23 has a third cold air passage 231, and the third seal fin 5 is provided in the third cold air passage 231 to block the high pressure chamber 121 and the low pressure chamber 122.
As shown in fig. 4, the third cold air path 231 has third and fourth sidewalls 2311 and 2312 with a ventilation gap between the third sealing fin 5 and the third and fourth sidewalls 2311 and 2312. Specifically, the cold air in the high pressure chamber 121 can enter the low pressure chamber 122 from the air permeable gap between the third sealing sheet 5 and the third and fourth sidewalls 2311 and 2312, that is, the cold air in the high pressure chamber 121 can enter the low pressure chamber 122 through the third cold air channel 231, so that the high pressure chamber 121 can input the cold air to the low pressure chamber 122.
It can be understood that the cold air pressure of the enclosed area among the first sealing sheet 3, the second sealing sheet and the third sealing sheet 5 is greater than the gas pressure of the area corresponding to the first cooling channel 21 in the gas channel 11, so as to ensure that the gas in the gas channel 11 does not invade the low-pressure cavity 122 from the first cold air channel 21, and further to isolate the low-pressure cavity 122 from the high-pressure cavity 121 and the area corresponding to the first cooling channel 21 in the gas channel 11.
Therefore, the pressure P2 of the cold air in the low pressure chamber 122 is greater than P5 and less than P3, and the cold air in the low pressure chamber 122 can prevent the gas in the gas channel 11 from entering the low pressure chamber 122, so the pressure difference between the low pressure chamber 122 and the corresponding areas of the gas channel 11 and the second cold air channel 22 is small, thereby reducing the leakage amount of the cold air in the second cold air channel 22, reducing the usage amount of the cold air, and further improving the cooling efficiency of the gas turbine.
In some embodiments, as shown in fig. 2, the second sealing piece 4 is provided inside the first sealing piece 3, the second sealing piece 4 is in contact with the first sealing piece 3 on one side in the axial direction of the body 1, and the second sealing piece 4 has a predetermined distance from the first sealing piece 3 on the other side in the axial direction of the body 1, so that the gap is wedge-shaped.
Specifically, as shown in fig. 1, the second sealing sheet 4 is disposed on a side of the first sealing sheet 3 pointing to the center of the body 1, wherein a right side of the second sealing sheet 4 is in contact with the first sealing sheet 3, and a left side of the second sealing sheet 4 is spaced apart from the first sealing sheet 3, that is, an included angle is formed between the first sealing sheet 3 and the second sealing sheet 4, so that a gap between the first sealing sheet 3 and the second sealing sheet 4 is wedge-shaped.
Therefore, the cold air in the high-pressure chamber 121 can enter the gap between the second seal fin 4 and the first seal fin 3, and does not or hardly leak at the contact position between the second seal fin 4 and the first seal fin 3.
In addition, the cold air in the high-pressure cavity 121 enters the gap between the first sealing sheet 3 and the second sealing sheet 4, so that the gas in the gas channel 11 cannot enter the low-pressure cavity 122 from the ventilation gap between the first sealing sheet 3 and the first side wall 211 and the second side wall 212 and the ventilation gap between the second sealing sheet 4 and the first side wall 211 and the second side wall 212, and further, the gas in the gas channel 11 cannot enter the low-pressure cavity 122 from the first cold air channel 21.
It is understood that there may be a gap at the contact position of the second seal fin 4 and the first seal fin 3, and the cold air in the high pressure chamber 121 may leak from the gap, but the gap is wedge-shaped, so the size of the gap is small, and the amount of cold air leaking from the gap is small, so the influence on the cooling efficiency of the gas turbine according to the embodiment of the present invention is small.
Specifically, the included angle formed between the first sealing fin 3 and the second sealing fin 4 is smaller than 90 °.
In some embodiments, the third cold air passage 231 communicates with the first cold air passage 21, and the outer side (the side away from the center of the body 1) of the third sealing sheet 5 is connected with the other side of the second sealing sheet 4. Specifically, the third seal fin 5 is connected to the left side of the second seal fin 4 on the side close to the second seal fin 4 in the radial direction of the body 1.
In some embodiments, as shown in fig. 3 and 4, the first side wall 211 has a first seal groove 2111 and a second seal groove 2112, the second side wall 212 has a third seal groove 2121 and a fourth seal groove 2122, the first seal sheet 3 includes a first mounting portion 31 and a second mounting portion 32, the first mounting portion 31 is disposed in the first seal groove 2111, and the second mounting portion 32 is disposed in the third seal groove 2121. The second seal fin 4 includes a third mounting portion 41 and a fourth mounting portion 42, the third mounting portion 41 being provided in the second seal groove 2112, and the fourth mounting portion 42 being provided in the fourth seal groove 2122.
The third side wall 2311 has a fifth seal groove 23111, the fourth side wall 2312 has a sixth seal groove 23121, the third seal fin 5 includes a fifth mounting portion 51 and a sixth mounting portion 52, the fifth mounting portion 51 is disposed in the fifth seal groove 23111, and the sixth mounting portion 52 is disposed in the sixth seal groove 23121.
Air gaps are provided between the first mounting portion 31 and the wall surface of the first seal groove 2111, between the second mounting portion 32 and the wall surface of the third seal groove, between the third mounting portion 41 and the wall surface of the second seal groove 2112, between the fourth mounting portion 42 and the wall surface of the fourth seal groove 2122, between the fifth mounting portion 51 and the wall surface of the fifth seal groove 23111, and between the sixth mounting portion 52 and the wall surface of the sixth seal groove 23121.
That is, the air-permeable gap between the first mounting portion 31 and the wall surface of the first seal groove 2111 and the air-permeable gap between the second mounting portion 32 and the wall surface of the third seal lip are air-permeable gaps between the first seal fin 3 and the first and second side walls 211 and 212; a gas-permeable gap between the third mounting portion 41 and the wall surface of the second seal groove 2112 and a gas-permeable gap between the fourth mounting portion 42 and the wall surface of the fourth seal groove 2122 are gas-permeable gaps between the second seal fin 4 and the first and second side walls 211 and 212; a ventilation gap between the fifth mounting portion 51 and the wall surface of the fifth seal groove 23111 and a ventilation gap between the sixth mounting portion 52 and the wall surface of the sixth seal groove 23121 are ventilation gaps between the third seal fin 5 and the third and fourth side walls 2311 and 2312.
In some embodiments, as shown in FIG. 5, a gas turbine according to embodiments of the present invention further includes a stationary blade set 6 and a moving blade set 7.
The stationary blade group 6 includes a plurality of stationary blades 61, the plurality of stationary blades 61 are provided in the gas passage 11 at intervals in the circumferential direction of the main body 1, the stationary blades 61 include stationary blade lower edge plates 611, and the first cold air passage 21 is formed between two stationary blade lower edge plates 611 adjacent in the circumferential direction of the main body 1.
Specifically, the cold air chamber 12 is located inside the vane lower edge plate 611, and there is a gap between two vane lower edge plates 611 adjacent in the circumferential direction of the body 1, the gap being a first cold air passage 21, wherein the first sealing sheet 3 and the second sealing sheet 4 are provided inside the first cold air passage 21.
The stationary blade group 6 and the moving blade group 7 are arranged at intervals in the axial direction of the body 1, the moving blade group 7 includes a plurality of moving blades 71, the plurality of moving blades 71 are provided at intervals in the circumferential direction of the body 1 in the combustion gas passage 11, the moving blades 71 include a moving blade lower edge plate 711, the first partition 2 includes a vane lower edge plate 611 and a moving blade lower edge plate 711, and the second cold air passage 22 is formed between the vane lower edge plate 611 and the moving blade lower edge plate 711.
Specifically, the vane lower edge plate 611 and the blade lower edge plate 711 have a gap in the axial direction of the body 1, the gap is the second cold air passage 22, and the cold air in the low pressure chamber 122 leaks into the gas passage 11 through the second cold air passage 22, so that the gas in the gas passage 11 is prevented from entering the low pressure chamber 122 through the second cold air passage 22.
It is understood that the cold air from the cold air chamber 12 can also exchange heat with the stationary blades 61 and the moving blades 71, thereby cooling the stationary blades 61 and the moving blades 71.
Further, each of the stationary blade group 6 and the moving blade group 7 may be plural, wherein 1 stationary blade group 6 and 1 moving blade group 7 are one blade group, the stationary blade group 6 is located on the left side of the moving blade group 7, and the plural blade groups are provided at intervals in the axial direction of the body 1. Wherein the vane lower rims 611 of the plurality of stationary blade groups 6 and the moving blade lower rims 711 of the plurality of moving blade groups 7 form the first partition 2.
In some embodiments, as shown in fig. 5, the stationary blade 61 further includes partition plates 612, the partition plates 612 being provided inside the stationary blade lower edge plate 611, the second partitions 23 include the partition plates 612, and the third cold air passage 231 is formed between two partition plates 612 adjacent in the circumferential direction of the body 1.
Specifically, a gap is formed between two partition plates 612 adjacent in the circumferential direction of the body 1, the gap is a third cold air passage 231, a third sealing sheet 5 is provided in the third cold air passage 231, and a plurality of partition plates 612 arranged at intervals in the circumferential direction of the body 1 form a second partition 23 partitioning the cold air chamber 12 into a high pressure chamber 121 and a low pressure chamber 122, wherein cold air in the high pressure chamber 121 can enter the low pressure chamber 122 through the third sealing sheet 5.
In some embodiments, the stationary blade 61 further includes a stationary blade body, the stationary blade body is provided with an air inlet channel, the air inlet channel communicates with the cold air inlet and the cold air source, that is, the cold air delivered from the cold air source enters the cold air chamber 12 through the air inlet channel, and the cold air can also exchange heat with the stationary blade 61, thereby cooling the stationary blade 61.
A gas turbine according to an embodiment of the present invention includes a gas turbine according to any of the above embodiments. In addition, the gas turbine of the embodiment of the invention also comprises a compressor and a combustion chamber. Specifically, the compressor continuously compresses external air, and inputs the compressed air into the combustion chamber, where the compressed air is mixed with fuel and burned to form high-temperature gas, and then flows into the gas turbine in any of the above embodiments to expand and do work, pushing the turbine blades to rotate and outputting mechanical work.
In the description of the present invention, it is to be understood that the terms "central," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," "circumferential," and the like are used in the orientations and positional relationships indicated in the drawings for convenience in describing the invention and to simplify the description, and are not intended to indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and are therefore not to be considered limiting of the invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally formed; may be mechanically coupled, may be electrically coupled or may be in communication with each other; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In the present invention, unless otherwise expressly stated or limited, the first feature "on" or "under" the second feature may be directly contacting the first and second features or indirectly contacting the first and second features through an intermediate. Also, a first feature "on," "over," and "above" a second feature may be directly or diagonally above the second feature, or may simply indicate that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature may be directly under or obliquely under the first feature, or may simply mean that the first feature is at a lesser elevation than the second feature.
In the present disclosure, the terms "one embodiment," "some embodiments," "an example," "a specific example," or "some examples" and the like mean that a specific feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present disclosure. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples and features of different embodiments or examples described in this specification can be combined and combined by one skilled in the art without contradiction.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made to the above embodiments by those of ordinary skill in the art within the scope of the present invention.
Claims (10)
1. A gas turbine, comprising:
a body having a gas passage and a cold gas cavity comprising a high pressure cavity and a low pressure cavity, the high pressure cavity and the low pressure cavity being spaced apart in an axial direction of the body;
the body is provided with a peripheral wall which is sleeved on the first partition part, the gas channel is formed between the peripheral wall and the first partition part, the first partition part is provided with the cold air cavity, the first partition part is provided with a cold air inlet communicated with the high pressure cavity, the cold air inlet is used for being communicated with a cold air source, the first partition part is further provided with a first cold air channel and a second cold air channel, the first cold air channel is provided with a first side wall and a second side wall, each of the high pressure cavity and the low pressure cavity is communicated with the gas channel through the first cold air channel, and the low pressure cavity is further communicated with the gas channel through the second cold air channel;
the first sealing sheet is arranged in the first cold air channel to block the gas channel from the high-pressure cavity and the gas channel from the low-pressure cavity, and a ventilation gap is formed between the first sealing sheet and the first side wall and between the first sealing sheet and the second side wall;
the second gasket, the second gasket is established in the first air conditioning passageway, in order to the separation the gas passageway with the low pressure chamber, first gasket with have between the second gasket with the gap of high pressure chamber intercommunication, the second gasket with first lateral wall with air permeable gap has between the second lateral wall.
2. The gas turbine of claim 1, wherein the first partition includes a second partition located between the high-pressure chamber and the low-pressure chamber in an axial direction of the body to partition the high-pressure chamber and the low-pressure chamber.
3. The gas turbine of claim 2, further comprising a third seal fin, the second partition having a third cold gas passage, the third cold gas passage having a third sidewall and a fourth sidewall, the third seal fin being disposed within the third cold gas passage to block the high pressure chamber and the low pressure chamber, the third seal fin having a gas permeable gap with the third sidewall and the fourth sidewall.
4. The gas turbine according to claim 3, wherein the second seal fin is provided inside the first seal fin, the second seal fin being in contact with the first seal fin on one side in the axial direction of the body, the second seal fin having a predetermined distance from the first seal fin on the other side in the axial direction of the body, so that the gap is wedge-shaped.
5. The gas turbine of claim 4, wherein the third cold gas passage communicates with the first cold gas passage, and an outer side of the third seal fin is connected to the other side of the second seal fin.
6. The gas turbine of claim 4, wherein the first sidewall has a first seal groove and a second seal groove, the second sidewall has a third seal groove and a fourth seal groove, the first sealing fin includes a first mounting portion and a second mounting portion, the first mounting portion is disposed in the first seal groove, the second mounting portion is disposed in the third seal groove, the second sealing fin includes a third mounting portion and a fourth mounting portion, the third mounting portion is disposed in the second seal groove, the fourth mounting portion is disposed in the fourth seal groove, the third sidewall has a fifth seal groove, the fourth sealing fin includes a fifth mounting portion and a sixth mounting portion, the fifth mounting portion is disposed in the fifth seal groove, the sixth mounting portion is disposed in the sixth seal groove,
the first installation department with between the wall of first seal groove, the second installation department with between the wall of third seal groove, the third installation department with between the wall of second seal groove, the fourth installation department with between the wall of fourth seal groove, the fifth installation department with between the wall of fifth seal groove and the sixth installation department with have air permeable gap between the wall of sixth seal groove.
7. The gas turbine of claim 3, further comprising:
a stationary blade group including a plurality of stationary blades provided in the gas passage at intervals in a circumferential direction of the body, the stationary blades including stationary blade lower edge plates, the first cold air passage being formed between two of the stationary blade lower edge plates adjacent in the circumferential direction of the body; and
and a moving blade group that is disposed at intervals in an axial direction of the body, the moving blade group including a plurality of moving blades that are provided at intervals in a circumferential direction of the body in the gas passage, the moving blades including a moving blade lower edge plate, the first partition including the stationary blade lower edge plate and the moving blade lower edge plate, the second cold air passage being formed between the stationary blade lower edge plate and the moving blade lower edge plate.
8. The gas turbine according to claim 7, wherein the stationary blade further includes a partition plate provided inside the stationary blade lower edge plate, the second partition portion includes the partition plate, and the third cold air passage is formed between two circumferentially adjacent partition plates of the body.
9. The gas turbine as set forth in claim 7, wherein said stationary blade further includes a stationary blade body provided with an intake passage communicating said cold air inlet and said cold air source.
10. A gas turbine comprising a gas turbine as claimed in claims 1 to 9.
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| CN202111201203.3A CN114087072B (en) | 2021-10-15 | 2021-10-15 | Gas turbine and gas turbine with same |
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| CN202111201203.3A CN114087072B (en) | 2021-10-15 | 2021-10-15 | Gas turbine and gas turbine with same |
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