Testing device for small-sized gas turbine test

Abstract

The invention discloses a small gas turbine experiment testing device which comprises a turbine shell and a shell assembly and further comprises a turbine rotor. The turbine rotor comprises a turbine shaft and a turbine disc arranged on the turbine shaft in a sleeving mode, and the turbine disc is located in the turbine shell. One end of the turbine shaft extends out of the shell assembly; a flow guide part is further installed in the turbine shell, an annular cavity is formed among the flow guide part, the turbine disc and the turbine shell, an annular cavity outlet is further formed in the turbine shell, and the annular cavity outlet is communicated with the annular cavity. According to the testing device for the small gas turbine test, the internal structure is simplified, the structure is compact, the connection strength is high, interference of external factors can be effectively reduced, energy loss except for a tested piece is reduced, and the influence of external loss on a test result is reduced. The turbine performance test can be conveniently carried out, and the gas turbine test performance of a small rocket engine can be obtained.

Description

Technical Field

[0001] This invention relates to the field of turbine performance testing technology, and more specifically to a small gas turbine testing device. Background Technology

[0002] Gas turbines, as power components in rocket engines, experience extremely high dynamic loads. Ground-based development and testing cannot provide the same operating environment as real-world conditions; therefore, operating conditions are typically scaled down to a fraction of the actual operating conditions before testing. For gas turbines in small rocket engines, the dynamic load during reduced-condition testing will be far lower than the turbine's design operating condition, resulting in a significant reduction in power. This leads to a higher proportion of external factors, such as mechanical losses and test bench vibrations, significantly impacting the test results. Furthermore, the limited internal space of small rocket engine turbines prevents the arrangement of numerous test structures as in high-power turbine test setups. Therefore, a compact, high-strength, and effectively reduced-interference-from-external-factors small gas turbine test setup is needed to conduct turbine performance tests and obtain experimental performance data for small rocket engine gas turbines. Summary of the Invention

[0003] To address the shortcomings of existing technologies, the present invention aims to provide a small gas turbine testing device, thereby solving the problem of the lack of a device capable of conducting reduced-condition testing on small rocket engine turbines.

[0004] To solve the above-mentioned technical problems, the present invention adopts the following technical solution: a small gas turbine test device, including a turbine housing and a housing assembly connected in series, and a turbine rotor disposed in the turbine housing and the housing assembly.

[0005] One end of the housing assembly extends into the turbine housing.

[0006] The turbine rotor includes a turbine shaft that extends through the turbine housing and housing assembly, and a turbine disk that is sleeved on the turbine shaft, the turbine disk being located inside the turbine housing.

[0007] One end of the turbine shaft extends out of the housing assembly, and the other end extends out of the turbine housing.

[0008] A flow guide is also installed inside the turbine housing, and the flow guide is installed on one end of the housing assembly that extends into the turbine housing.

[0009] An annular cavity is formed between the guide member, the turbine disk, and the turbine housing. An annular cavity outlet is also provided on the outer surface of the turbine housing, and the annular cavity outlet is connected to the annular cavity.

[0010] The present invention also has the following technical features: A first bearing and a second bearing are also installed between the turbine shaft and the housing assembly. The inner rings of the first bearing and the second bearing are mounted on the turbine shaft, and the outer rings of the first bearing and the second bearing are fitted onto the inner wall of the housing assembly.

[0011] The first bearing is located on the side closer to the turbine housing, and the second bearing is located on the side farther from the turbine housing.

[0012] An inner ring sleeve and an outer ring sleeve are installed between the first bearing and the second bearing. The inner ring sleeve is fitted onto the turbine shaft, and the outer ring sleeve is fitted onto the inner wall of the housing assembly.

[0013] The inner ring of the first bearing on the side opposite to the second bearing is limited by an adjusting shim and the turbine shaft. The outer ring of the second bearing on the side opposite to the first bearing is limited by a bearing limiting nut. The bearing limiting nut is threadedly connected to the inner wall of the housing assembly.

[0014] The end of the housing assembly facing away from the turbine housing is also covered with a fixing cap.

[0015] The fixed cover is connected via a first flange, which is mounted on the outer surface of the housing assembly, and the turbine shaft extends through the fixed cover.

[0016] A torque transmission sleeve is also fitted onto one end of the turbine shaft that protrudes from the fixed pressure cover. The torque transmission sleeve includes a sleeve section and a flange section that are connected together. The flange section is splinedly connected to the turbine shaft.

[0017] One end of the sleeve section facing away from the flange section contacts the inner ring of the second bearing.

[0018] The fixed pressure cap is sleeved on the outside of the torque transmission sleeve.

[0019] The turbine shaft is also equipped with a shaft end nut at one end that protrudes from the torque transmission sleeve. The shaft end nut is used to limit the axial movement of the torque transmission sleeve.

[0020] The turbine rotor is mounted on a mounting ring at one end of the housing assembly, and a first seal is installed between the mounting ring and the turbine shaft.

[0021] A second seal is installed between the fixed pressure cap and the torque transmission sleeve.

[0022] A turbine end nut is installed at one end of the turbine shaft that protrudes from the turbine housing, and a positioning ring is also fitted on the outer surface of the turbine shaft that protrudes from the turbine housing. The positioning ring contacts the groove on the turbine disk.

[0023] One end of the turbine disk, which is sleeved on the turbine shaft, contacts the stepped surface on the turbine shaft for axial limiting, while the other end is axially limited by the turbine end nut and the positioning ring.

[0024] The turbine housing and housing assembly are connected by a second flange, which is mounted on the outer surface of the housing assembly.

[0025] A third flange is also installed on the first flange, and the third flange is installed on the side of the first flange facing away from the turbine housing.

[0026] The housing assembly is also provided with cooling passages, which include cooling passages formed in the inner wall of the housing assembly and drainage passages formed in the inner wall of the housing assembly.

[0027] The cooling path is closed at one end and connected to the gap between the first bearing and the housing assembly at the other end. The drain path is closed at one end and open at the other end and connected to the gap between the fixed pressure cap and the housing assembly at the other end.

[0028] The cooling passage also includes a cooling passage inlet and a drain outlet on the housing assembly, wherein the cooling passage inlet is connected to the cooling passage and the drain outlet is connected to the drain outlet.

[0029] The fixed pressure cover is also equipped with several positioning blocks on the side facing away from the housing assembly. The positioning blocks are provided with positioning holes, and positioning elements are inserted into the positioning holes. The positioning elements are threadedly connected to the positioning holes, and one end of the positioning elements extends into the annular positioning groove opened on the outside of the flange section.

[0030] Compared with the prior art, the present invention has the following technical effects: (I) The present invention provides a small gas turbine test device that simplifies the internal structure, achieves a compact structure, high connection strength, effectively reduces interference from external factors, reduces energy loss other than that of the tested component, and reduces the impact of external losses on the test results. It can conveniently conduct turbine performance tests and obtain the gas turbine test performance of small rocket engines. Attached Figure Description

[0031] Figure 1 This is a schematic diagram of the overall structure of the small gas turbine test apparatus of the present invention. Figure I .

[0032] Figure 2 This is a schematic diagram of the overall structure of the small gas turbine test apparatus of the present invention. Figure II .

[0033] Figure 3 This is a schematic diagram of the structure of the torque transmission sleeve of the present invention.

[0034] The meanings of the labels in the attached diagram are as follows: 1-Turbine housing, 2-Housing assembly, 3-Turbine rotor, 4-Guide element, 5-Annular cavity, 6-Annular cavity outlet, 7-First bearing, 8-Second bearing, 9-Inner ring sleeve, 10-Outer ring sleeve, 11-Adjusting shim, 12-Bearing limit nut, 13-Fixing gland, 14-First flange, 15-Torque transmission sleeve, 16-Shaft end nut, 17-First seal, 18-Second seal, 19-Turbine end nut, 20-Positioning ring, 21-Second flange, 22-Third flange, 23-Cooling passage, 24-Positioning block, 25-Positioning hole, 26-Positioning element.

[0035] 3-1-Turbine shaft, 3-2-Turbine disk.

[0036] 15-1-Sleeve section, 15-2-Flange section, 15-3-Annular positioning groove.

[0037] 23-1-Cooling path, 23-2-Drainage path, 23-3-Cooling path inlet, 23-4-Drainage path outlet.

[0038] The specific content of the present invention will be further explained in detail below with reference to the embodiments. Detailed Implementation

[0039] Unless otherwise specified, all components in this invention are components known in the prior art.

[0040] The following are specific embodiments of the present invention. It should be noted that the present invention is not limited to the following specific embodiments. All equivalent modifications made based on the technical solutions of this application fall within the protection scope of the present invention.

[0041] Example 1: This embodiment provides a small gas turbine testing device, such as... Figures 1-2 As shown, it includes a turbine housing 1 and a housing assembly 2 connected together, and also includes a turbine rotor 3 disposed within the turbine housing 1 and the housing assembly 2.

[0042] One end of the housing assembly 2 extends into the turbine housing 1.

[0043] The turbine rotor 3 includes a turbine shaft 3-1 that passes through the turbine housing 1 and the housing assembly 2, and a turbine disk 3-2 that is sleeved on the turbine shaft 3-1. The turbine disk 3-2 is located inside the turbine housing 1. The turbine disk 3-2 is provided with internal splines and mates with the turbine shaft 3-1.

[0044] One end of the turbine shaft 3-1 extends out of the housing assembly 2, and the other end extends out of the turbine housing 1.

[0045] The turbine housing 1 is also equipped with a flow guide 4, which is installed on one end of the housing assembly 2 that extends into the turbine housing 1.

[0046] An annular cavity 5 is formed between the flow guide 4, the turbine disk 3-2 and the turbine housing 1. An annular cavity outlet 6 is also provided on the outer surface of the turbine housing 1, and the annular cavity outlet 6 is connected to the annular cavity 5.

[0047] Both ends of the turbine housing 1 and housing assembly 2 are open. During operation, the turbine shaft 3-1 is connected to the test bench shaft system, and gas is introduced into the turbine housing 1, driving the turbine disk 3-2 to rotate, which in turn drives the turbine shaft 3-1 to rotate. By using the test bench to record the speed changes, the torque and axial force characteristics of the turbine, as well as the turbine efficiency, are obtained. Pressure sensors, temperature sensors, and flow meters can also be installed at the medium inlet and outlet of the turbine casing to obtain relevant parameters such as the curve of the flow area changing with the pressure ratio and speed ratio, thereby obtaining the actual performance of the turbine and providing data for rocket parameter balancing.

[0048] As a preferred embodiment: A first bearing 7 and a second bearing 8 are also installed between the turbine shaft 3-1 and the housing assembly 2. The inner rings of the first bearing 7 and the second bearing 8 are installed on the turbine shaft 3-1, and the outer rings of the first bearing 7 and the second bearing 8 are sleeved on the inner wall of the housing assembly 2.

[0049] The first bearing 7 and the second bearing 8 are both roller bearings.

[0050] As a preferred embodiment: The first bearing 7 is located on the side closer to the turbine housing 1, and the second bearing 8 is located on the side farther away from the turbine housing 1.

[0051] An inner ring sleeve 9 and an outer ring sleeve 10 are installed between the first bearing 7 and the second bearing 8. The inner ring sleeve 9 is sleeved on the turbine shaft 3-1, and the outer ring sleeve 10 is sleeved on the inner wall of the housing assembly 2.

[0052] The inner ring of the first bearing 7 facing away from the second bearing 8 is limited by the adjusting shim 11 and the turbine shaft 3-1. The outer ring of the second bearing 8 facing away from the first bearing 7 is limited by the bearing limiting nut 12. The bearing limiting nut 12 is threadedly connected to the inner wall of the housing assembly 2.

[0053] The inner ring sleeve 9, outer ring sleeve 10, adjusting shim 11, bearing limit nut 12, and the stepped surface of turbine shaft 3-1 together complete the limiting of the first bearing 7 and the second bearing 8.

[0054] As a preferred embodiment: The housing assembly 2, facing away from the turbine housing 1, is also covered with a fixing cap 13.

[0055] The fixed cover 13 is connected by a first flange 14, which is installed on the outer surface of the housing assembly 2, and the turbine shaft 3-1 extends out of the fixed cover 13.

[0056] As a preferred embodiment: The turbine shaft 3-1 is also fitted with a torque transmission sleeve 15 at one end that protrudes from the fixed pressure cover 13. The torque transmission sleeve 15 includes a sleeve section 15-1 and a flange section 15-2 that are connected together. The flange section 15-2 is splinedly connected to the turbine shaft 3-1.

[0057] One end of the sleeve section 15-1 facing away from the flange section 15-2 is in contact with the inner ring of the second bearing 8.

[0058] The fixed pressure cap 13 is sleeved on the outside of the torque transmission sleeve 15.

[0059] The turbine shaft 3-1 is also equipped with a shaft end nut 16 at one end that extends out of the torque transmission sleeve 15. The shaft end nut 16 is used to limit the axial movement of the torque transmission sleeve 15.

[0060] Torque sleeve 15 is used to connect turbine shaft 3-1 to the shaft system of the test bench.

[0061] The fixed pressure cover 13 and the housing assembly 2 are provided with sealing elements.

[0062] As a preferred embodiment: The turbine rotor 3 is mounted on a mounting ring at one end of the housing assembly 2, and a first seal 17 is installed between the mounting ring and the turbine shaft 3-1.

[0063] A second seal 18 is installed between the fixed pressure cap 13 and the torque transmission sleeve 15.

[0064] The first seal 17 includes a bidirectional seal and a retaining ring; the bidirectional seal is assembled inside the housing assembly 2 and is interference-fitted with the turbine shaft 3-1 at a corresponding position; the bidirectional seal is located at one end near the turbine disk 3-2; the retaining ring is installed on the housing assembly 2, on the side of the bidirectional seal near the turbine disk 3-2, to prevent axial displacement of the bidirectional seal. The second seal 18 is a unidirectional seal and is interference-fitted with the turbine shaft 3-1.

[0065] As a preferred embodiment: A turbine end nut 19 is installed at one end of the turbine shaft 3-1 that protrudes from the turbine housing 1. A positioning ring 20 is also fitted on the outer surface of the turbine shaft 3-1 that protrudes from the turbine housing 1. The positioning ring 20 contacts the groove on the turbine disk 3-2.

[0066] One end of the turbine disk 3-2, which is sleeved on the turbine shaft 3-1, contacts the stepped surface on the turbine shaft 3-1 for axial limiting, and the other end is axially limited by the turbine end nut 19 and the positioning ring 20.

[0067] As a preferred embodiment: The turbine housing 1 and housing assembly 2 are connected by a second flange 21, which is mounted on the outer surface of the housing assembly 2.

[0068] A third flange 22 is also installed on the first flange 14, and the third flange 22 is installed on the side of the first flange 14 facing away from the turbine housing 1.

[0069] As a preferred embodiment: The housing assembly 2 is also provided with a cooling passage 23, which includes a cooling passage 23-1 opened in the inner wall of the housing assembly 2 and an outlet passage 23-2 opened in the inner wall of the housing assembly 2.

[0070] The cooling path 23-1 is closed at one end and connected to the gap between the first bearing 7 and the housing assembly 2 at the other end. The drain path 23-2 is closed at one end and open at the other end and connected to the gap between the fixed pressure cover 13 and the housing assembly 2.

[0071] The cooling passage 23 also includes a cooling passage inlet 23-3 and a drain outlet 23-4 formed on the housing assembly 2. The cooling passage inlet 23-3 is connected to the cooling passage 23-1, and the drain outlet 23-4 is connected to the drain passage 23-2.

[0072] The housing assembly has 2 to 3 cooling channels 23-1 and drainage channels 23-2, which are evenly distributed along the circumference.

[0073] During the experiment, cooling water was introduced through the cooling inlet 23-3. The cooling water flowed out along the cooling inlet 23-3, cooling channel 23-1, first bearing 7, the gap between inner ring sleeve 9 and outer ring sleeve 10, second bearing 8, the gap between bearing limit nut 12, the gap between fixed cover 13 and housing assembly 2, drain channel 23-2 and drain outlet 23-4.

[0074] As a preferred embodiment: The fixed pressure cover 13 is also equipped with several positioning blocks 24 on the side facing away from the housing assembly 2. The positioning blocks 24 are provided with positioning holes 25. Positioning elements 26 are inserted into the positioning holes 25. The positioning elements 26 are threadedly connected to the positioning holes 25. One end of the positioning element 24 extends into the annular positioning groove 15-3 opened on the outside of the flange section 15-2.

[0075] The specific working process of this invention: A small gas turbine testing device.

[0076] A third flange 22 is provided at the left end of the housing assembly 2 for connection to the test bench mounting bracket, and a second flange 21 at the right end is connected to the turbine housing 2. Simultaneously, a total of four seals are provided to form a closed inner cavity: a bidirectional seal near the turbine disk 3-2 to prevent bearing cooling water and turbine combustion gas from leaking into the cavity; a seal and a bevel seal on the torque transmission sleeve 15 to seal the left end of the cooling circuit; and a stepped seal on the turbine housing 2 to prevent combustion gas leakage.

[0077] The turbine disk 3-2 is splined to the turbine shaft 3-1. A locating ring 20 is provided to strengthen the connection and positioning between the turbine disk 3-2 and the turbine shaft 3-1. Two bearings are provided for shaft support. An adjusting shim 11 is provided to adjust the shaft position, ensuring the test clearance is within the required range. A positioning component 24 cooperates with a torque transmission sleeve 15 to limit the maximum displacement of the shaft. The turbine end nut 19 and the shaft end nut 16 are used to tighten the shaft components. A locking groove can also be provided for mechanical locking to prevent the shaft from loosening during the test. During operation, the torque transmission sleeve 15 on the turbine shaft 3-1 is connected to the test bench shaft system, and gas is introduced into the turbine housing 1, which drives the turbine disk 3-2 to rotate, thereby driving the turbine shaft 3-1 to rotate. By using the test bench to measure the speed change, the torque and axial force characteristics of the turbine and the turbine efficiency are obtained. Cooling water is then connected, and the cooling water cools the two bearings in sequence along the flow path before being discharged from the drain outlet on the other side. This process cools the bearings.

[0078] Pressure sensors, temperature sensors, and flow meters can also be installed at the medium inlet and outlet of the turbine housing 1 to obtain relevant parameters such as the curve of the flow area changing with the pressure ratio and speed ratio, thereby obtaining the actual performance of the turbine and providing data for rocket parameter balancing.

[0079] The testing device should have a simplified internal structure as much as possible to reduce energy loss other than that of the device under test and to minimize the impact of external losses on the test results.

[0080] The above technical solutions are merely preferred embodiments of the present invention, but the scope of protection of the present invention is not limited thereto. Any changes or substitutions conceived by those skilled in the art within the scope of the technology disclosed in the present invention without creative effort are covered within the scope of protection of the present invention.

Claims

1. A small gas turbine testing device, characterized in that, It includes a turbine housing (1) and a housing assembly (2) connected together, and a turbine rotor (3) disposed within the turbine housing (1) and the housing assembly (2); One end of the housing assembly (2) extends into the turbine housing (1); The turbine rotor (3) includes a turbine shaft (3-1) that passes through the turbine housing (1) and the housing assembly (2) and a turbine disk (3-2) sleeved on the turbine shaft (3-1), wherein the turbine disk (3-2) is located inside the turbine housing (1); One end of the turbine shaft (3-1) extends out of the housing assembly (2); The turbine housing (1) is also equipped with a flow guide (4), which is installed on one end of the housing assembly (2) that extends into the turbine housing (1); An annular cavity (5) is formed between the flow guide (4), the turbine disk (3-2) and the turbine housing (1). An annular cavity outlet (6) is also provided on the outer surface of the turbine housing (1), and the annular cavity outlet (6) is connected to the annular cavity (5).

2. The small gas turbine testing apparatus as described in claim 1, characterized in that, A first bearing (7) and a second bearing (8) are also installed between the turbine shaft (3-1) and the housing assembly (2). The inner rings of the first bearing (7) and the second bearing (8) are installed on the turbine shaft (3-1), and the outer rings of the first bearing (7) and the second bearing (8) are sleeved on the inner wall of the housing assembly (2).

3. The small gas turbine testing apparatus as described in claim 2, characterized in that, The first bearing (7) is located on the side closer to the turbine housing (1), and the second bearing (8) is located on the side farther away from the turbine housing (1). An inner ring sleeve (9) and an outer ring sleeve (10) are installed between the first bearing (7) and the second bearing (8). The inner ring sleeve (9) is fitted onto the turbine shaft (3-1), and the outer ring sleeve (10) is fitted onto the inner wall of the housing assembly (2). The inner ring of the first bearing (7) facing away from the second bearing (8) is limited by the adjusting shim (11) and the turbine shaft (3-1). The outer ring of the second bearing (8) facing away from the first bearing (7) is limited by the bearing limiting nut (12). The bearing limiting nut (12) is threadedly connected to the inner wall of the housing assembly (2).

4. The small gas turbine testing apparatus as described in claim 3, characterized in that, The housing assembly (2) is also covered with a fixing cap (13) at the end facing away from the turbine housing (1); The fixed cover (13) is connected by a first flange (14), which is mounted on the outer surface of the housing assembly (2), and the turbine shaft (3-1) extends out of the fixed cover (13).

5. The small gas turbine testing apparatus as described in claim 4, characterized in that, The turbine shaft (3-1) is also fitted with a torque transmission sleeve (15) at one end that protrudes from the fixed pressure cover (13). The torque transmission sleeve (15) includes a sleeve section (15-1) and a flange section (15-2) that are connected together. The flange section (15-2) is splinedly connected to the turbine shaft (3-1). The sleeve section (15-1) is in contact with the inner ring of the second bearing (8) at one end facing away from the flange section (15-2); The fixed pressure cap (13) is sleeved on the outside of the torque transmission sleeve (15); The turbine shaft (3-1) is also equipped with a shaft end nut (16) at one end that protrudes from the torque transmission sleeve (15). The shaft end nut (16) is used to limit the axial movement of the torque transmission sleeve (15).

6. The small gas turbine testing apparatus as described in claim 5, characterized in that, The turbine rotor (3) is mounted on a mounting ring at one end of the housing assembly (2), and a first seal (17) is installed between the mounting ring and the turbine shaft (3-1). A second seal (18) is installed between the fixed pressure cap (13) and the torque transmission sleeve (15).

7. The small gas turbine testing apparatus as described in claim 1, characterized in that, The turbine shaft (3-1) is also equipped with a turbine end nut (19) at one end of the turbine housing (1), and a positioning ring (20) is also fitted on the outer surface of the turbine shaft (3-1) at one end of the turbine housing (1), and the positioning ring (20) contacts the groove on the turbine disk (3-2). The turbine disk (3-2) is sleeved on the turbine shaft (3-1) at one end, which contacts the stepped surface on the turbine shaft (3-1) for axial limiting, and the other end is axially limited by the turbine end nut (19) and the positioning ring (20).

8. The small gas turbine testing apparatus as described in claim 4, characterized in that, The turbine housing (1) and housing assembly (2) are connected by a second flange (21), which is mounted on the outer surface of the housing assembly (2); A third flange (22) is also installed on the first flange (14), and the third flange (22) is installed on the side of the first flange (14) facing away from the turbine housing (1).

9. The small gas turbine testing apparatus as described in claim 2, characterized in that, The housing assembly (2) is also provided with a cooling passage (23), which includes a cooling passage (23-1) opened in the inner wall of the housing assembly (2) and an outlet passage (23-2) opened in the inner wall of the housing assembly (2). The cooling path (23-1) is closed at one end and connected to the gap between the first bearing (7) and the housing assembly (2) at the other end. The drain path (23-2) is closed at one end and open at the other end and connected to the gap between the fixed pressure cap (13) and the housing assembly (2). The cooling passage (23) further includes a cooling passage inlet (23-3) and a drain outlet (23-4) opened on the housing assembly (2), wherein the cooling passage inlet (23-3) is connected to the cooling passage (23-1) and the drain outlet (23-4) is connected to the drain passage (23-2).

10. The small gas turbine testing apparatus as described in claim 5, characterized in that, The fixed pressure cover (13) is also equipped with several positioning blocks (24) on the side facing away from the housing assembly (2). The positioning blocks (24) are provided with positioning holes (25). Positioning elements (26) are inserted into the positioning holes (25). The positioning elements (26) are threadedly connected to the positioning holes (25). One end of the positioning element (24) extends into the annular positioning groove (15-3) opened on the outside of the flange section (15-2).

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