A test device for a gas turbine combustion chamber nozzle

Abstract

The present invention discloses a device for testing a nozzle in a gas turbine combustion chamber, the device comprising a reverse rectifying portion and a flow equalizing plate. The reverse rectifying portion comprises a nozzle mounting portion and a first chamber, a transition chamber, and a second chamber that are sequentially connected, the first chamber being located upstream of the transition chamber, the second chamber being located downstream of the transition chamber, the first chamber being connected to a source of combustion-supporting gas, the flow equalizing plate being located at the outlet of the transition chamber and / or at the inlet of the second chamber, and the flow equalizing plate having a plurality of vents for the combustion-supporting gas to flow through. The device for testing a nozzle in a gas turbine combustion chamber according to an embodiment of the present invention has advantages such as high reliability.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbine combustion, and in particular to a nozzle testing device for a gas turbine combustion chamber. Background Art

[0002] The technical development of gas turbine combustors is inseparable from combustor testing. Nozzle performance testing is the most fundamental means of verifying the feasibility of combustion system designs, and uniformity of airflow at the nozzle inlet is a key requirement of nozzle testing. However, prior art suffers from low airflow uniformity at the nozzle outlet, leading to issues such as low reliability of combustor nozzle test data. Summary of the Invention

[0003] The present invention is based on the inventor's discovery and understanding of the following facts and problems:

[0004] A gas turbine is a rotary internal combustion engine consisting primarily of a compressor, combustion chamber, and turbine. Air flows backward through the compressor exhaust chamber into the annular canal-shaped combustion chamber. Then, it enters the premixing chamber of the fuel nozzle. The injected fuel and air mix before entering the combustion tube of the combustion chamber and burning. The high-temperature gas is discharged through the transition section.

[0005] The development of gas turbine combustors involves both microscopic chemical kinetics and macroscopic turbulent flows, with the two being strongly nonlinearly coupled. Current combustion theories and methods struggle to accurately quantitatively analyze the operating characteristics of combustors under real-world conditions, including ignition characteristics, stability boundaries, combustion efficiency, and structural integrity. Therefore, achieving the optimal design with low NOx emissions, low combustion pulsation, a wide operating margin, and a long life requires multiple rounds of design optimization iterations, with design solutions validated and confirmed through numerical simulation and experimental testing. Testing is the ultimate criterion for verifying design correctness. Single-nozzle experimental research can help us understand nozzle design principles and experimental verification techniques, enabling us to complete preliminary, optimized, and refined nozzle design for the combustor nozzle.

[0006] The nozzle test setup needs to simulate the fluid dynamics at the nozzle inlet under real-world conditions to create the desired airflow structure. Currently, related technologies lack uniformity at the nozzle inlet. This inconsistency in the nozzle inlet environment can lead to significant differences in the oil-gas mixing and distribution at the nozzle compared to a real combustion chamber.

[0007] The present invention aims to at least partially address one of the technical problems in the related art. To this end, embodiments of the present invention provide a gas turbine combustor nozzle testing device to improve the reliability of combustor nozzle test data.

[0008] A gas turbine combustion chamber nozzle test device according to an embodiment of the present invention includes a reverse rectifying part and a flow equalizing plate. The reverse rectifying part includes a nozzle mounting portion and a first chamber, a transition chamber, and a second chamber that are connected in sequence. The nozzle mounting portion is used to mount a nozzle for fuel to flow through. The first chamber is located upstream of the transition chamber, and the second chamber is located downstream of the transition chamber. The first chamber is connected to a gas source of a combustion-supporting gas, wherein the flow direction of the combustion-supporting gas in the first chamber intersects with the flow direction of the combustion-supporting gas in the second chamber, and the flow direction of the combustion-supporting gas in the transition chamber intersects with the flow direction of the combustion-supporting gas in the first chamber, and the flow direction of the combustion-supporting gas in the transition chamber is opposite to or intersects with the flow direction of the combustion-supporting gas in the second chamber. The flow equalizing plate is located at the outlet of the transition chamber and / or at the inlet of the second chamber, and the flow equalizing plate has a plurality of vents for the combustion-supporting gas to flow through.

[0009] In some embodiments, there are multiple equalizing plates, at least one equalizing plate is provided at the outlet of the transition chamber, and at least one equalizing plate is provided at the inlet of the second chamber.

[0010] In some embodiments, the extension direction of the transition chamber is perpendicular to the extension direction of the first chamber, so that the flow direction of the combustion-supporting gas in the first chamber is perpendicular to the flow direction of the combustion-supporting gas in the transition chamber, and the extension direction of the transition chamber is parallel to the extension direction of the second chamber, so that the flow direction of the combustion-supporting gas in the second chamber is opposite to the flow direction of the combustion-supporting gas in the transition chamber.

[0011] In some embodiments, the flow balancing plate provided at the outlet of the transition chamber is perpendicular to the flow balancing plate provided at the inlet of the first chamber.

[0012] In some embodiments, the flow equalizing plate provided at the outlet of the transition chamber is parallel to the extension direction of the transition chamber, and the flow equalizing plate provided at the inlet of the second chamber is perpendicular to the extension direction of the second chamber.

[0013] In some embodiments, the transition chamber and the second chamber are both annular chambers, and the flow balancing plate is an annular flow balancing plate.

[0014] In some embodiments, the flow equalizing plate has a plurality of vent hole groups, each of the vent hole groups includes a plurality of the vent holes, and the plurality of vent hole groups are evenly spaced along the radial direction of the flow equalizing plate.

[0015] In some embodiments, the plurality of vent holes in the same vent hole group are evenly spaced along the circumference of the flow equalizing plate.

[0016] In some embodiments, the sum of the flow areas of the plurality of vents in any one of the vent groups is equal to the sum of the flow areas of the plurality of vents in any other one of the vent groups.

[0017] In some embodiments, the reverse rectification part also includes a first cylinder, a second cylinder, a first annular sealing plate and a second annular sealing plate, the first cylinder is arranged outside the second cylinder, the first cylinder and the second cylinder are spaced apart in the inner and outer directions, the first cylinder has a first port and a second port opposite to each other in its extension direction, the second cylinder has a third port and a fourth port opposite to each other in its extension direction, the fourth port is located between the first port and the second port in the extension direction of the first cylinder, and the first port is located between the third port and the fourth port in the extension direction of the first cylinder.

[0018] The first sealing plate and the second sealing plate are arranged at intervals along the extension direction of the first cylinder, the outer end of the first sealing plate is connected to the first cylinder, and the inner end of the first sealing plate is connected to the second cylinder, the second sealing plate and the second cylinder are arranged at intervals along the extension direction of the first cylinder, the outer end of the second sealing plate is connected to the first cylinder, and the inner end of the second sealing plate extends to the interior of the second cylinder, so that the transition chamber is defined between the first cylinder, the second cylinder, the first sealing plate and the second sealing plate.

[0019] The first cylinder has an opening communicating with the first chamber, the opening forms an inlet of the transition chamber, the second cylinder and the second sealing plate define an outlet of the transition chamber, and the second chamber is located in the second cylinder.

[0020] In some embodiments, the reverse rectification part also includes a third cylinder, the second cylinder is arranged outside the third cylinder, the third cylinder and the second cylinder are spaced apart in the inner and outer directions, the third cylinder has a fifth port and a sixth port opposite to each other in the extension direction of the first cylinder, the fifth port is located between the third port and the fourth port in the extension direction of the first cylinder, and the fifth port is arranged closer to the third port relative to the sixth port in the extension direction of the first cylinder, the inner end of the second sealing plate is connected to the third cylinder, and the second chamber is defined between the second cylinder, the second sealing plate and the third cylinder.

[0021] In some embodiments, the reverse rectifying portion further includes a third chamber, which is located downstream of the second chamber. The flow direction of the combustion-supporting gas in the third chamber is opposite to the flow direction of the combustion-supporting gas in the second chamber.

[0022] In some embodiments, the reverse rectifying portion further includes an annular third sealing plate, which seals the third port and has an inner hole for at least a portion of the nozzle to pass through, so that the third cylinder and the nozzle define the third chamber.

[0023] In some embodiments, a combustion-supporting gas pipeline is further included. The combustion-supporting gas pipeline is arranged upstream of the transition chamber, and at least a portion of the combustion-supporting gas pipeline defines the first chamber.

[0024] In some embodiments, a plurality of the combustion-supporting gas pipelines are provided, and the plurality of the combustion-supporting gas pipelines are arranged at intervals along the circumference of the nozzle mounting portion. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 It is a front view of a gas turbine combustion chamber nozzle testing device according to an embodiment of the present invention.

[0026] Figure 2 It is a right side view of a gas turbine combustion chamber nozzle testing device according to an embodiment of the present invention.

[0027] Figure 3 This is a structural schematic diagram of a first flow equalizing plate for a gas turbine combustion chamber nozzle testing device according to an embodiment of the present invention.

[0028] Figure 4 This is a structural schematic diagram of a second flow equalizing plate for a gas turbine combustion chamber nozzle testing device according to an embodiment of the present invention.

[0029] Reference numerals:

[0030] A gas turbine combustion chamber nozzle testing device 100;

[0031] Reverse rectification part 1, nozzle mounting portion 101; first chamber 102; transition chamber 103; second chamber 104; third chamber 105; fourth chamber 106; fifth chamber 107;

[0032] Nozzle 2;

[0033] Flow balancing plate 3; first flow balancing plate 301; first vent 3011; second flow balancing plate 302; second vent 3021;

[0034] First cylinder 4; first port 401; second port 402;

[0035] Second cylinder 5; third port 501; fourth port 502;

[0036] The third cylinder 6; the fifth port 601; the sixth port 602;

[0037] First sealing plate 7;

[0038] Second sealing plate 8;

[0039] The third sealing plate 9; inner hole 901;

[0040] Combustion-supporting gas pipeline 10; first pipe section 1001; second pipe section 1002; third pipe section 1003;

[0041] Air intake portion 11;

[0042] Combustion part 12; small diameter section 1201; large diameter section 1202. DETAILED DESCRIPTION

[0043] The embodiments of the present invention are described in detail below, and examples of the embodiments are shown in the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary and intended to be used to explain the present invention, but should not be understood as limiting the present invention.

[0044] The technical solution of the present application is described in detail below with reference to the accompanying drawings.

[0045] like Figures 1 to 4 As shown, a gas turbine combustion chamber nozzle testing device 100 according to an embodiment of the present invention includes a reverse rectifying part 1 and a flow balancing plate 3 .

[0046] The reverse flow rectifying section 1 includes a nozzle mounting portion 101 and a first chamber 102, a transition chamber 103, and a second chamber 104, which are connected in sequence. The nozzle mounting portion 101 is used to mount the nozzle 2 through which the fuel flows. The first chamber 102 is located upstream of the transition chamber 103, and the second chamber 104 is located downstream of the transition chamber 103. The first chamber 102 is connected to a source of combustion-supporting gas. The flow direction of the combustion-supporting gas in the first chamber 102 intersects with the flow direction of the combustion-supporting gas in the second chamber 104. The flow direction of the combustion-supporting gas in the transition chamber 103 intersects with the flow direction of the combustion-supporting gas in the first chamber 102. The flow direction of the combustion-supporting gas in the transition chamber 103 is opposite to or intersects with the flow direction of the combustion-supporting gas in the second chamber 104.

[0047] The flow balancing plate 3 is provided at the outlet of the transition chamber 103 and / or the inlet of the second chamber 104 , and has a plurality of vent holes for the combustion-supporting gas to flow through.

[0048] The equalizing plate 3 is provided at the outlet of the transition chamber 103 and / or the inlet of the second chamber 104. This can be understood as: the equalizing plate 3 is provided only at the outlet of the transition chamber 103; or, the equalizing plate is provided only at the inlet of the second chamber 104; or, the equalizing plate 3 is provided at both the outlet of the transition chamber 103 and the inlet of the second chamber 104. By using the equalizing plate 3 provided at the outlet of the transition chamber 103 and / or the inlet of the second chamber 104, the combustion-supporting gas at the outlet of the second chamber 104 can be made more uniform.

[0049] When the performance of the nozzle 2 is tested using a gas turbine combustion chamber nozzle testing device 100 according to an embodiment of the present invention, the nozzle 2 to be tested is installed on the nozzle mounting portion 101. The fuel enters the nozzle through the inlet of the nozzle 2. The combustion-supporting gas enters the first chamber 102 through the inlet of the first chamber 102, and then enters the transition chamber 103 and the second chamber 104 in sequence. When the combustion-supporting gas flowing out of the outlet of the second chamber 104 is mixed with the fuel ejected from the outlet of the nozzle 2, the combustion-supporting gas at the outlet of the second chamber 104 has better uniformity, which can improve the uniformity of the mixing of the combustion-supporting gas and the fuel, thereby improving the reliability of the gas turbine combustion chamber nozzle testing device 100 according to an embodiment of the present invention.

[0050] Therefore, the gas turbine combustion chamber nozzle testing device 100 according to the embodiment of the present invention has advantages such as high reliability.

[0051] Optionally, the combustion-supporting gas may be compressed air or compressed oxygen.

[0052] In some embodiments, the transition chamber 103 and the second chamber 104 are both annular chambers, and the flow equalizing plate 3 is an annular flow equalizing plate.

[0053] By configuring the transition chamber 103 and the second chamber 104 as annular chambers, when the combustion-supporting gas enters the transition chamber 103 from the first chamber 102, it first diffuses in an annular manner and then enters the second chamber 104 through the annular flow equalizing plate. The combustion-supporting gas entering the second chamber 104 diffuses in an annular manner again, thereby increasing the flow uniformity of the combustion-supporting gas, which is beneficial to improving the uniformity of the mixing of the combustion-supporting gas and the fuel, and is beneficial to improving the reliability of a gas turbine combustion chamber nozzle testing device 100 according to an embodiment of the present invention.

[0054] In some embodiments, a plurality of flow balancing plates 3 are provided, at least one flow balancing plate 3 is provided at the outlet of the transition chamber 103 , and at least one flow balancing plate 3 is provided at the inlet of the second chamber 104 .

[0055] For example, Figure 1As shown, two equalizing plates 3 are provided, namely a first equalizing plate 301 and a second equalizing plate 302. The first equalizing plate 301 is provided at the outlet of the transition chamber 103, and the second equalizing plate 302 is provided at the inlet of the second chamber 104. The combustion-supporting gas in the transition chamber 103 flows out of the transition chamber 103 through the first equalizing plate 301, improving the flow uniformity of the combustion-supporting gas. The combustion-supporting gas flowing out of the transition chamber 103 flows into the second chamber 104 through the second equalizing plate 302, further improving the flow uniformity of the combustion-supporting gas.

[0056] Therefore, by setting up a multi-stage flow equalizing plate 3, the combustion-supporting gas entering the second chamber 104 is evenly distributed, thereby further improving the flow uniformity of the combustion-supporting gas and further improving the reliability of the gas turbine combustion chamber nozzle testing device 100 according to an embodiment of the present invention.

[0057] In some embodiments, the extension direction of the transition chamber 103 is perpendicular to the extension direction of the first chamber 102, so that the flow direction of the combustion-supporting gas in the first chamber 102 is perpendicular to the flow direction of the combustion-supporting gas in the transition chamber 103. The extension direction of the transition chamber 103 is parallel to the extension direction of the second chamber 104, so that the flow direction of the combustion-supporting gas in the second chamber 104 is opposite to the flow direction of the combustion-supporting gas in the transition chamber 103.

[0058] In order to make the technical solution of the present application easier to understand, the following further describes the technical solution of the present application by taking the example that the extension direction of the transition chamber 103 is consistent with the left-right direction and the extension direction of the first chamber 102 is consistent with the inside-outside direction, wherein the left-right direction and the inside-outside direction are as follows. Figure 1 and Figure 3 As shown, inward refers to a direction adjacent to the center line of the first chamber 102 on a plane perpendicular to the center line of the first chamber 102 , and outward refers to a direction away from the center line of the first chamber 102 on a plane perpendicular to the center line of the first chamber 102 .

[0059] For example, Figure 1 As shown, the combustion-supporting gas flows into the first chamber 102 from outside to inside, and the combustion-supporting gas flowing out of the outlet of the first chamber 102 flows into the transition chamber 103 from left to right and flows out from the outlet of the transition chamber 103 through the first flow equalizing plate 301, and then the combustion-supporting gas flows into the second chamber 104 from right to left through the second flow equalizing plate 302.

[0060] Therefore, by setting the flow direction of the combustion-supporting gas in the second chamber 104 opposite to the flow direction of the combustion-supporting gas in the transition chamber 103, it is beneficial to increase the flow uniformity of the combustion-supporting gas, thereby further improving the reliability of the gas turbine combustion chamber nozzle testing device 100 of an embodiment of the present invention.

[0061] Optionally, the flow balancing plate 3 provided at the outlet of the transition chamber 103 is perpendicular to the flow balancing plate 3 provided at the inlet of the first chamber 102 .

[0062] For example, the first current balancing plate 301 is perpendicular to the second current balancing plate 302 .

[0063] By vertically arranging the first flow balancing plate 301 and the second flow balancing plate 302 , the flow uniformity of the combustion-supporting gas can be further improved.

[0064] In some embodiments, the equalizing plate 3 provided at the outlet of the transition chamber 103 is parallel to the extension direction of the transition chamber 103 , and the equalizing plate 3 provided at the inlet of the second chamber 104 is perpendicular to the extension direction of the first chamber 102 .

[0065] For example, Figure 1 、 Figure 3 and Figure 4 As shown, the first equalizing plate 301 is an annular equalizing plate extending in the left-right direction. In other words, the first equalizing plate 301 is a equalizing tube. The axial direction of the first equalizing plate 301 is parallel to the left-right direction. The tube wall of the first equalizing plate 301 has multiple first vents 3011, which extend in the inside-out direction. The second equalizing plate 302 is an annular equalizing plate extending in the inside-out direction. The second equalizing plate 302 has multiple second vents 3021, which extend in the left-right direction.

[0066] When the combustion-supporting gas in the annular transition chamber 103 flows out through the first flow equalizing plate 301, the first flow equalizing plate 301 is used to increase the flow uniformity of the combustion-supporting gas in the inward and outward directions. When the combustion-supporting gas flowing out of the transition chamber 103 enters the annular second chamber 104 through the second flow equalizing plate 302, the second flow equalizing plate 302 is used to increase the flow uniformity of the combustion-supporting gas in the left and right directions.

[0067] Therefore, by increasing the flow uniformity of the combustion-supporting gas in the inward and outward directions and the left and right directions, the reliability of the gas turbine combustion chamber nozzle testing device 100 according to the embodiment of the present invention is further improved.

[0068] Alternatively, as Figure 3 As shown, the first air vents 3011 of the first flow equalizing plate 301 are provided in multiple groups, each group of first air vents 3011 includes multiple first air vents 3011, the multiple first air vents 3011 in the same group are evenly spaced along the circumference of the first flow equalizing plate 301, and the multiple groups of first air vents 3011 are evenly spaced along the left-right direction.

[0069] Alternatively, as Figure 2 and Figure 4As shown, the second vent holes 3021 of the second flow equalizing plate 302 are provided with multiple groups, each group of second vent holes 3021 includes multiple second vent holes 3021, and the multiple second vent holes 3021 in the same group are evenly spaced along the circumference of the second flow equalizing plate 302, and multiple groups of second vent holes 3021 are evenly spaced along the inside-outside direction.

[0070] Optionally, the sum of the flow areas of the plurality of second vent holes 3021 in any one group is equal to the sum of the flow areas of the plurality of second vent holes 3021 in any other group.

[0071] In some embodiments, the reverse rectification part 1 further includes a first cylinder 4, a second cylinder 5, an annular first sealing plate 7 and an annular second sealing plate 8. The first cylinder 4 is sleeved outside the second cylinder 5, and the first cylinder 4 and the second cylinder 5 are spaced apart in the inward and outward directions, wherein inward refers to the direction in which the plane perpendicular to the axis of the first cylinder 4 is adjacent to the axis of the first cylinder 4, and outward refers to the direction in which the plane perpendicular to the axis of the first cylinder 4 is away from the axis of the first cylinder 4. The first cylinder 4 has a first port 401 and a second port 402 opposite to each other in the direction of its extension. The second cylinder 5 has a third port 501 and a fourth port 502 opposite to each other in the direction of its extension, and the fourth port 502 is located between the first port 401 and the second port 402 in the direction of its extension of the first cylinder 4, and the first port 401 is located between the third port 501 and the fourth port 502 in the direction of its extension of the first cylinder 4.

[0072] The first sealing plate 7 and the second sealing plate 8 are spaced apart along the extension direction of the first cylinder 4. The outer end of the first sealing plate 7 is connected to the first cylinder 4, and the inner end of the first sealing plate 7 is connected to the second cylinder 5. The second sealing plate 8 and the second cylinder 5 are spaced apart along the extension direction of the first cylinder 4. The outer end of the second sealing plate 8 is connected to the first cylinder 4, and the inner end of the second sealing plate 8 extends into the interior of the second cylinder 5, so that a transition chamber 103 is defined between the first cylinder 4, the second cylinder 5, the first sealing plate 7, and the second sealing plate 8.

[0073] The first cylinder 4 has an opening communicating with the first chamber 102 , which forms the inlet of the transition chamber 103 . The outlet of the transition chamber 103 is defined between the second cylinder 5 and the second sealing plate 8 . The second chamber 104 is located in the second cylinder 5 .

[0074] For example, Figure 1 As shown, the first port 401 is located at the left end of the second port 402, and the third port 501 is located at the left end of the fourth port 502. The first sealing plate 7 and the second sealing plate 8 are spaced apart in the left-right direction. The first sealing plate 7 blocks the first port 401, and the second sealing plate 8 blocks the second port 402 and the fourth port 502, so that the inner circumference of the first cylinder 4, the outer circumference of the second cylinder 5, the right end surface of the first sealing plate 7, and the left end surface of the second sealing plate 8 define a transition chamber 103.

[0075] Therefore, a gas turbine combustion chamber nozzle testing device 100 according to an embodiment of the present invention is configured to form an annular space by arranging a first cylinder 4, a second cylinder 5, a first sealing plate 7 and a second sealing plate 8, thereby improving the flow uniformity of the combustion-supporting gas and making the gas turbine combustion chamber nozzle testing device 100 according to an embodiment of the present invention simple in structure.

[0076] Optionally, the opening on the first cylinder 4 and the first flow equalizing plate 301 are spaced apart in the left-right direction.

[0077] For example, Figure 1 As shown, the opening on the first cylinder 4 is located on the left side of the first flow equalizing plate 301 to prevent the combustion-supporting gas in the first chamber 102 from directly impacting the first vent hole 3011 on the first flow equalizing plate 301 and affecting the flow equalizing effect of the first flow equalizing plate 301.

[0078] In some embodiments, the reverse rectifying portion 1 further includes a third cylinder 6. The second cylinder 5 is sleeved outside the third cylinder 6, and the third cylinder 6 and the second cylinder 5 are spaced apart in the inner and outer directions. The third cylinder 6 has a fifth port 601 and a sixth port 602 that are opposite to each other in the extension direction of the first cylinder 4. The fifth port 601 is located between the third port 501 and the fourth port 502 in the extension direction of the first cylinder 4. The fifth port 601 is located closer to the third port 501 than the sixth port 602 in the extension direction of the first cylinder 4. The inner end of the second sealing plate 8 is connected to the third cylinder 6, and a second chamber 104 is defined between the second cylinder 5, the second sealing plate 8, and the third cylinder 6.

[0079] For example, Figure 1 As shown, the fifth port 601 and the sixth port 602 are spaced apart in the left-right direction, with the fifth port 601 located to the left of the sixth port 602. The third port 501 and the fifth port 601 are spaced apart in the left-right direction, with the third port 501 located to the left of the fifth port 601. The inner circumferential surface of the second barrel 5, the outer circumferential surface of the third barrel 6, and the left end surface of the second sealing plate 8 define a second chamber 104.

[0080] Therefore, a gas turbine combustion chamber nozzle testing device 100 according to an embodiment of the present invention is configured to have a third cylinder 6, thereby configuring the second chamber 104 to be an annular space. This improves the flow uniformity of the combustion-supporting gas while further simplifying the structure of the gas turbine combustion chamber nozzle testing device 100 according to an embodiment of the present invention.

[0081] Optionally, each of the first cylinder 4 , the second cylinder 5 and the third cylinder 6 is coaxially arranged.

[0082] In some embodiments, the reverse rectifying part 1 further includes a third chamber 105 , which is located downstream of the second chamber 104 , and the flow direction of the combustion-supporting gas in the third chamber 105 is opposite to that in the second chamber 104 .

[0083] For example, Figure 1 As shown, the combustion-supporting gas enters the second chamber 104 through the transition chamber 103, and then enters the third chamber 105. Since the flow direction of the combustion-supporting gas in the second chamber 104 is opposite to that in the third chamber 105, that is, the combustion-supporting gas entering the second chamber 104 enters the third chamber 105 in the opposite direction, thereby achieving reverse rectification of the combustion-supporting gas by the reverse rectification part 1.

[0084] Thus, the gas turbine combustor nozzle testing device 100 according to the embodiment of the present invention reversely rectifies the combustion-supporting gas entering the reverse rectifying portion 1 before mixing it with the fuel ejected from the nozzle 2. While improving the flow uniformity of the combustion-supporting gas, it also realistically simulates the airflow structure at the nozzle 2, maintaining consistency between the nozzle 2 test conditions and the actual operating environment of the gas turbine, further improving the accuracy of the nozzle 2 performance test data, and thus further enhancing the reliability of the gas turbine combustor nozzle testing device 100 according to the embodiment of the present invention.

[0085] Optionally, the reverse rectification part 1 further includes an annular third sealing plate 9, which seals the third port 501 and has an inner hole 901 for at least a portion of the nozzle 2 to pass through, so that the third cylinder 6 and the nozzle 2 define a third chamber 105.

[0086] For example, a flange is provided on the nozzle 2, and a plurality of blind holes are provided on the third sealing plate 9. The flange and the blind holes are connected by bolts, thereby fixing the nozzle 2 to the third sealing plate 9. The nozzle 2 penetrates the inner hole 901 of the third sealing plate 9 in the left-right direction, and the nozzle opening of the nozzle 2 is placed in the third barrel 6, so that a third chamber 105 is formed between the inner circumference of the third barrel 6 and the outer circumference of the nozzle 2.

[0087] Therefore, by setting the third sealing plate 9 to block the third port 501, a third chamber 105 is defined between the third cylinder 6 and the nozzle 2, further making the gas turbine combustion chamber nozzle testing device 100 of the embodiment of the present invention simple in structure and reasonable in layout.

[0088] Optionally, a gas turbine combustor nozzle testing device 100 according to an embodiment of the present invention further includes an air intake portion 11 and a combustion portion 12. The air intake portion 11 is communicated with the first chamber 102, and the air intake portion 11 allows combustion-supporting gas to enter. The combustion portion 12 is communicated with the third chamber 105, so that the combustion-supporting gas and fuel are mixed and burned to form high-temperature combustion gas. The combustion-supporting gas entering the third chamber 105 is mixed with the fuel ejected from the nozzle 2 and burns in the combustion portion 12 to form high-temperature combustion gas.

[0089] In some embodiments, the reverse rectification part 1 also includes a fourth chamber 106 connected to the first chamber 102. The fourth chamber 106 is arranged upstream of the first chamber 102. The fourth chamber 106 is used to connect with the gas source of the combustion-supporting gas. The flow direction of the combustion-supporting gas in the fourth chamber 106 intersects with the flow direction of the combustion-supporting gas in the first chamber 102.

[0090] For example, Figure 1 As shown, the combustion-supporting gas of the air intake part 11 enters the first chamber 102 through the fourth chamber 106. By setting the fourth chamber 106, the air intake part 11 and the first chamber 102 are connected, thereby further making the gas turbine combustion chamber nozzle testing device 100 of the embodiment of the present invention simple in structure and easy to connect.

[0091] In some embodiments, the reverse rectification part 1 also includes a fifth chamber 107 connected to the fourth chamber 106. The fifth chamber 107 is arranged upstream of the fourth chamber 106. The fifth chamber 107 is used to connect with the gas source of the combustion-supporting gas. The flow direction of the combustion-supporting gas in the fifth chamber 107 intersects with the flow direction of the combustion-supporting gas in the fourth chamber 106.

[0092] For example, Figure 1 As shown, the combustion-supporting gas in the air intake part 11 enters the fourth chamber 106 through the fifth chamber 107. By setting the fourth chamber 106 and the fifth chamber 107, the combustion-supporting gas in the air intake part 11 can be further facilitated to enter the first chamber 102, so that the gas turbine combustion chamber nozzle testing device 100 of the embodiment of the present invention has a simple structure and is easy to connect.

[0093] Optionally, the extension direction of the first chamber 102 is perpendicular to the extension direction of the second chamber 104 , so that the flow direction of the combustion-supporting gas in the first chamber 102 is perpendicular to the flow direction of the combustion-supporting gas in the second chamber 104 .

[0094] Optionally, the extension direction of the fourth chamber 106 is perpendicular to the extension direction of the first chamber 102 , so that the flow direction of the combustion-supporting gas in the fourth chamber 106 is perpendicular to the flow direction of the combustion-supporting gas in the first chamber 102 .

[0095] Optionally, the extension direction of the fifth chamber 107 is perpendicular to the extension direction of the fourth chamber 106 , so that the flow direction of the combustion-supporting gas in the fifth chamber 107 is perpendicular to the flow direction of the combustion-supporting gas in the fourth chamber 106 .

[0096] For example, Figure 1 As shown, the extension direction of the first chamber 102 is perpendicular to the extension direction of the second chamber 104, the extension direction of the fourth chamber 106 is perpendicular to the extension direction of the first chamber 102, and the extension direction of the fifth chamber 107 is perpendicular to the extension direction of the fourth chamber 106. The combustion-supporting gas in the air intake portion 11 is deflected 90 degrees and enters the fifth chamber 107. The combustion-supporting gas in the fifth chamber 107 is deflected 90 degrees and then enters the fourth chamber 106. The combustion-supporting gas in the fourth chamber 106 is deflected 90 degrees and then enters the first chamber 102. The combustion-supporting gas in the first chamber 102 enters the transition chamber 103 in a side intake manner.

[0097] Therefore, by rationally arranging the first chamber 102 , the second chamber 104 , the third chamber 105 , the fourth chamber 106 and the fifth chamber 107 , the gas turbine combustion chamber nozzle testing device 100 according to the embodiment of the present invention has a simple structure and a rational layout.

[0098] In some embodiments, a gas turbine combustion chamber nozzle testing device 100 according to an embodiment of the present invention further includes a combustion-supporting gas pipeline 10, which is arranged upstream of a first chamber 102. The combustion-supporting gas pipeline 10 includes a first pipe segment 1001, a second pipe segment 1002, and a third pipe segment 1003 connected in sequence. The second pipe segment 1002 is arranged upstream of the first pipe segment 1001, and the third pipe segment 1003 is arranged upstream of the second pipe segment 1002. The first pipe segment 1001 defines a first chamber 102, the second pipe segment 1002 defines a fourth chamber 106, and the third pipe segment 1003 defines a fifth chamber 107.

[0099] Therefore, by forming the first pipe section 1001, the second pipe section 1002 and the third pipe section 1003 of the combustion-supporting gas pipeline 10 into the first chamber 102, the fourth chamber 106 and the fifth chamber 107 respectively, the gas turbine combustion chamber nozzle testing device 100 of the embodiment of the present invention has a simple structure and is easy to install.

[0100] Optionally, a plurality of combustion-supporting gas pipelines 10 are provided, and the plurality of combustion-supporting gas pipelines 10 are arranged at intervals along the circumference of the nozzle mounting portion 101 .

[0101] like Figure 1 and Figure 3 As shown, four combustion-supporting gas pipelines 10 are provided, and the four combustion-supporting gas pipelines 10 are evenly spaced along the circumference of the nozzle mounting portion 101 .

[0102] Thus, the combustion-supporting gas of the air intake part 11 enters the transition chamber 103 through multiple combustion-supporting gas pipelines 10, thereby improving the uniformity of the annular flow of the combustion-supporting gas in the transition chamber 103 and further improving the reliability of the gas turbine combustion chamber nozzle testing device 100 of an embodiment of the present invention.

[0103] Optionally, a plurality of combustion-supporting gas pipelines 10 are provided, and the plurality of combustion-supporting gas pipelines 10 are arranged at intervals along the circumference of the nozzle mounting portion 101 .

[0104] like Figure 1 and Figure 3 As shown, four combustion-supporting gas pipelines 10 are provided, and the four combustion-supporting gas pipelines 10 are evenly spaced along the circumference of the nozzle mounting portion 101 .

[0105] Thus, the combustion-supporting gas of the air intake part 11 enters the transition chamber 103 through multiple combustion-supporting gas pipelines 10, thereby improving the uniformity of the annular flow of the combustion-supporting gas in the transition chamber 103 and further improving the reliability of the gas turbine combustion chamber nozzle testing device 100 of an embodiment of the present invention.

[0106] Optionally, the air intake portion 11 is an air intake pipe, each combustion-supporting gas pipeline 10 is connected to the air intake pipe, and multiple combustion-supporting gas pipelines 10 are arranged around the center line of the air intake pipe.

[0107] By arranging multiple combustion-supporting gas pipelines 10 around the center line of the intake pipe, the intake working conditions of each combustion-supporting gas pipeline 10 can be made the same, thereby further improving the reliability of the gas turbine combustion chamber nozzle testing device 100 according to an embodiment of the present invention.

[0108] Optionally, the combustion part 12 is a combustion tube, and at least a portion of the combustion tube extends into the third cylinder 6 so that the third chamber 105 is in communication with the combustion part 12 .

[0109] Optionally, the combustion tube includes a large diameter section 1202 and a small diameter section 1201 , the large diameter section 1202 is arranged downstream of the small diameter section 1201 , and the small diameter section 1201 extends into the third cylinder 6 .

[0110] For example, Figure 1 As shown, the third barrel 6 is sleeved on the small diameter section 1201, and the third barrel 6 is connected to the small diameter section 1201. The combustion-supporting gas and the fuel sprayed from the nozzle 2 are mixed in the small diameter section 1201 and then enter the large diameter section 1202 for combustion. The high-temperature gas generated by the combustion in the large diameter section 1202 is discharged through the right port of the large diameter section 1202.

[0111] Therefore, by setting the combustion part 12 into a small-diameter section 1201 and a large-diameter section 1202, the structure is simple, which facilitates the mixed combustion-supporting gas and fuel in the third cylinder 6 to enter the combustion part 12 for combustion.

[0112] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like to indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0113] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features being referred to. 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, "plurality" means at least two, such as two, three, etc., unless otherwise specifically defined.

[0114] In the present invention, unless otherwise specified or limited, the terms "installed," "connected," "connect," "fixed," etc. should be understood in a broad sense. For example, they can refer to fixed connection, detachable connection, or integration; mechanical connection, electrical connection, or communication; direct connection or indirect connection through an intermediate medium; internal communication between two elements or interaction between two elements, unless otherwise specified. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0115] In the present invention, unless otherwise expressly specified or limited, when a first feature is "above" or "below" a second feature, it may mean that the first and second features are in direct contact, or that the first and second features are in indirect contact through an intermediary. Furthermore, when a first feature is "above," "above," or "above" a second feature, it may mean that the first feature is directly above or diagonally above the second feature, or simply means that the first feature is at a higher level than the second feature. When a first feature is "below," "below," or "below" a second feature, it may mean that the first feature is directly below or diagonally below the second feature, or simply means that the first feature is at a lower level than the second feature.

[0116] In the present invention, the terms "one embodiment", "some embodiments", "examples", "specific examples", or "some examples" mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic expressions of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art can combine and combine different embodiments or examples described in this specification and the features of different embodiments or examples without contradiction.

[0117] Although the above embodiments have been shown and described, it is understood that the above embodiments are illustrative and are not to be construed as limitations on the present invention. Changes, modifications, substitutions and variations of the above embodiments by those skilled in the art are all within the scope of protection of the present invention.

Claims

1. A gas turbine combustion chamber nozzle testing device, characterized in that: include: A reverse rectifying part, which includes a nozzle mounting portion and a first chamber, a transition chamber, a second chamber, a first cylinder, a second cylinder, an annular first sealing plate and an annular second sealing plate that are connected in sequence. The nozzle mounting portion is used to mount a nozzle for fuel to flow through. The first chamber is located upstream of the transition chamber, and the second chamber is located downstream of the transition chamber. The first chamber is connected to a gas source of a combustion-supporting gas, wherein the flow direction of the combustion-supporting gas in the first chamber intersects with the flow direction of the combustion-supporting gas in the second chamber, and the flow direction of the combustion-supporting gas in the transition chamber intersects with the flow direction of the combustion-supporting gas in the first chamber. , and the flow direction of the combustion-supporting gas in the transition chamber is opposite to or intersects with the flow direction of the combustion-supporting gas in the second chamber, the first cylinder is sleeved outside the second cylinder, the first cylinder and the second cylinder are spaced apart in the inner and outer directions, the first cylinder has a first port and a second port opposite to each other in the extension direction thereof, the second cylinder has a third port and a fourth port opposite to each other in the extension direction thereof, the fourth port is located between the first port and the second port in the extension direction of the first cylinder, and the first port is located between the third port and the fourth port in the extension direction of the first cylinder; and The first sealing plate and the second sealing plate are spaced apart along the extension direction of the first cylinder, the outer end of the first sealing plate is connected to the first cylinder, and the inner end of the first sealing plate is connected to the second cylinder, the second sealing plate and the second cylinder are spaced apart along the extension direction of the first cylinder, the outer end of the second sealing plate is connected to the first cylinder, and the inner end of the second sealing plate extends into the interior of the second cylinder, so that the transition chamber is defined between the first cylinder, the second cylinder, the first sealing plate and the second sealing plate; The first cylinder has an opening communicating with the first chamber, the opening forming an inlet of the transition chamber, the second cylinder and the second sealing plate define an outlet of the transition chamber, and the second chamber is located in the second cylinder; and A flow balancing plate is provided at the outlet of the transition chamber and / or the inlet of the second chamber, and has a plurality of vent holes for the combustion-supporting gas to flow through.

2. A gas turbine combustion chamber nozzle testing device according to claim 1, characterized in that: There are multiple flow balancing plates, at least one of which is arranged at the outlet of the transition chamber, and at least one of which is arranged at the inlet of the second chamber.

3. A gas turbine combustion chamber nozzle testing device according to claim 2, characterized in that: The extension direction of the transition chamber is perpendicular to the extension direction of the first chamber, so that the flow direction of the combustion-supporting gas in the first chamber is perpendicular to the flow direction of the combustion-supporting gas in the transition chamber. The extension direction of the transition chamber is parallel to the extension direction of the second chamber, so that the flow direction of the combustion-supporting gas in the second chamber is opposite to the flow direction of the combustion-supporting gas in the transition chamber.

4. A gas turbine combustion chamber nozzle testing device according to claim 3, characterized in that: The flow balancing plate provided at the outlet of the transition chamber is perpendicular to the flow balancing plate provided at the inlet of the first chamber.

5. The gas turbine combustion chamber nozzle testing device according to claim 4, characterized in that: The flow balancing plate provided at the outlet of the transition chamber is parallel to the extension direction of the transition chamber, and the flow balancing plate provided at the inlet of the second chamber is perpendicular to the extension direction of the second chamber.

6. A gas turbine combustion chamber nozzle testing device according to any one of claims 1 to 5, characterized in that: The transition chamber and the second chamber are both annular chambers, and the flow balancing plate is an annular flow balancing plate.

7. A gas turbine combustion chamber nozzle testing device according to claim 6, characterized in that: The flow balancing plate is provided with a plurality of vent hole groups, each of the vent hole groups includes a plurality of the vent holes, and the plurality of vent hole groups are evenly spaced along the radial direction of the flow balancing plate.

8. The gas turbine combustion chamber nozzle testing device according to claim 7, characterized in that: The plurality of vent holes in the same vent hole group are evenly spaced along the circumference of the flow equalizing plate.

9. The gas turbine combustion chamber nozzle testing device according to claim 7, characterized in that: The sum of the flow areas of the plurality of vent holes in any one of the vent hole groups is equal to the sum of the flow areas of the plurality of vent holes in any other one of the vent hole groups.

10. The gas turbine combustion chamber nozzle testing device according to claim 1, characterized in that: The reverse rectification part also includes: The third cylinder, the second cylinder is arranged outside the third cylinder, the third cylinder and the second cylinder are spaced apart in the inner and outer directions, the third cylinder has a fifth port and a sixth port opposite to each other in the extension direction of the first cylinder, the fifth port is located between the third port and the fourth port in the extension direction of the first cylinder, the fifth port is arranged closer to the third port relative to the sixth port in the extension direction of the first cylinder, the inner end of the second sealing plate is connected to the third cylinder, and the second chamber is defined between the second cylinder, the second sealing plate and the third cylinder.

11. A gas turbine combustion chamber nozzle testing device according to claim 10, characterized in that: The reverse rectifying part further includes a third chamber, which is arranged downstream of the second chamber. The flow direction of the combustion-supporting gas in the third chamber is opposite to the flow direction of the combustion-supporting gas in the second chamber.

12. A gas turbine combustion chamber nozzle testing device according to claim 11, characterized in that: The reverse rectifying part further includes an annular third sealing plate, which seals the third port and has an inner hole for at least a portion of the nozzle to pass through, so that the third cylinder and the nozzle define the third chamber.

13. A gas turbine combustion chamber nozzle testing device according to any one of claims 10-12, characterized in that: It also includes a combustion-supporting gas pipeline, which is arranged upstream of the transition chamber, and at least a portion of the combustion-supporting gas pipeline defines the first chamber.

14. A gas turbine combustion chamber nozzle testing device according to claim 13, characterized in that: There are multiple combustion-supporting gas pipelines, and the multiple combustion-supporting gas pipelines are arranged at intervals along the circumference of the nozzle mounting portion.

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