Aero-retrofit gas turbine engine-free installation tool and gas turbine

Abstract

The utility model provides an aero-reform gas turbine engine-free installation tool and a gas turbine. The aero-reform gas turbine engine-free installation tool comprises a main beam, a front connecting assembly, a rear connecting assembly, a centering dummy shaft, a centering supporting plate, a dial indicator and an engine simulation pipeline. A front connecting assembly, a rear connecting assembly, a centering dummy shaft and an engine simulation pipeline are installed on the main beam, a centering supporting plate is installed on the centering dummy shaft, and a dial indicator is arranged on the centering supporting plate; the limitation of the engine delivery date on the assembly work of the whole modified gas turbine generator set is eliminated, and it is guaranteed that the assembly work can still be smoothly carried out under the condition that no engine exists.

Description

Technical Field

[0001] The utility model relates to the field of gas turbine tooling, in particular to an aero-derivative gas turbine engine-free installation tooling and a gas turbine. Background Art

[0002] The aeroderivative gas turbine generator set consists of an aeroderivative gas turbine (also known as an engine), a generator and its auxiliary systems. The normal assembly sequence is: engine in place - install the engine on the base - drop the cover on the base and connect - engine pipe connection - engine electrical connection - engine and generator center installation - various auxiliary systems connection, and the assembly of the entire unit can be completed. The existing assembly technology is based on the premise that the engine is in place and installed first. If the engine is not in place, the assembly of the aeroderivative gas turbine generator set cannot be carried out at all.

[0003] Aero-derivative gas turbines are modified from aircraft engines and can only be completely imported at present. The delivery cycle is long and there are uncontrollable factors in the delivery period. The timely arrival of the engine cannot be guaranteed. If the engine is delivered late, it will affect the delivery cycle of the entire unit. If the assembly of domestic units is to be guaranteed, it is necessary to make import reserves of engines in advance. However, since the engine is expensive, the engine accounts for 40% of the cost of the unit, resulting in a large initial investment in the project. At the same time, the engine needs regular maintenance. The reserve of the engine is bound to bring corresponding maintenance costs. Therefore, it will be of great significance to develop an engine-free installation technology to eliminate the restrictions of the engine delivery period on the assembly of the entire unit and effectively guarantee the assembly of the entire unit. Utility Model Content

[0004] In view of the defects in the prior art, the purpose of the utility model is to provide an aeroderivative gas turbine engine-free installation tool and a gas turbine.

[0005] According to the utility model, an aero-derivative gas turbine engine-free installation tool is provided, comprising: a main beam, a front connection assembly, a rear connection assembly, a centering dummy shaft, a centering support plate, a dial indicator and an engine simulation pipeline;

[0006] The front connecting assembly, the rear connecting assembly, the centering dummy shaft and the engine simulation pipeline are installed on the main beam, the centering dummy shaft is installed on the centering support plate, and the centering support plate is provided with a dial indicator;

[0007] A gas turbine using the aeroderivative gas turbine engine-free installation tooling, comprising: a base, a casing, a front mounting leg assembly and a rear mounting leg assembly;

[0008] The front mounting leg assembly and the rear mounting leg assembly are mounted on a base, the cover shell is fixedly mounted on the base via a first fastening assembly, and the front mounting leg assembly and the rear mounting leg assembly are located inside the cover shell;

[0009] The main beam is placed in the cover shell, the front connecting assembly is connected to the front mounting leg assembly, and the rear connecting assembly is connected to the rear mounting leg assembly.

[0010] Preferably, the front connecting assembly is arranged on both sides close to one end of the main beam, and the rear connecting assembly is arranged at the other end of the main beam.

[0011] Preferably, the front connecting assembly comprises a front right connecting member and a front left connecting member, and the front right connecting member and the front left connecting member are respectively located on both sides of the main beam;

[0012] The rear connection assembly includes: a rear right connection piece, a rear lower connection piece, a rear left connection piece and a mounting plate;

[0013] The mounting plate is mounted on the main beam, and a rear right connecting piece, a rear lower connecting piece, and a rear left connecting piece are mounted on the mounting plate.

[0014] Preferably, reinforcing ribs are provided between the mounting plate and the main beam.

[0015] Preferably, the tooling front support and the tooling rear support are fixedly mounted on the main beam via a second fastening assembly, and the main beam is supported by the tooling front support and the tooling rear support.

[0016] Preferably, the front mounting leg assembly includes a front left mounting leg and a front right mounting leg, and the rear mounting leg assembly includes a rear left mounting leg assembly, a rear right mounting leg assembly and a rear lower mounting leg assembly;

[0017] The front left mounting leg is connected to the front left connecting piece, the front right mounting leg is connected to the front right connecting piece, the rear left mounting leg assembly is connected to the rear left connecting piece, the rear right mounting leg assembly is connected to the rear right connecting piece, and the rear lower mounting leg assembly is connected to the rear lower connecting piece.

[0018] Preferably, the interface pipe in the housing is connected to the engine simulation pipe, and the interface pipe includes a fuel pipe, an oil lubrication pipe and a gas pipe.

[0019] Preferably, the housing comprises: a housing body and a housing top plate;

[0020] The casing body is fixedly mounted on the base, and the casing top plate is detachably mounted on the casing body via fasteners.

[0021] Compared with the prior art, the utility model has the following beneficial effects:

[0022] 1. The tooling of the present application is easy to manufacture, simple in structure, low in cost, and easy to hoist and carry, thus reducing the risk of engine hoisting damage;

[0023] 2. This application eliminates the limitation of engine delivery period for the assembly of the entire modified gas turbine generator set, ensuring that the assembly work can proceed smoothly even without the engine;

[0024] 3. This application adopts a split cover design, which realizes the replacement installation of tooling and engine, reducing the workload of engine replacement;

[0025] 4. This application not only develops engine-free installation technology, but also allows pre-installation using tooling even when the engine has arrived, greatly reducing the difficulty of engine assembly;

[0026] 5. This application does not require the import and reserve of engines, which greatly reduces the engine investment cost in the early stage of the project. At the same time, it eliminates the regular maintenance items of the engine and reduces the maintenance cost of the engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Other features, objects and advantages of the present invention will become more apparent by reading the detailed description of non-limiting embodiments with reference to the following drawings:

[0028] Figure 1 This is the front view of the installation tooling for the aeroderivative gas turbine without engine;

[0029] Figure 2 A top view of the installation tooling for an aeroderivative gas turbine without an engine;

[0030] Figure 3 This is a side view of the installation tooling for an aeroderivative gas turbine without an engine;

[0031] Figure 4 Front view after engine installation for a conventional gas turbine;

[0032] Figure 5 This is a schematic diagram of the front mounting leg assembly;

[0033] Figure 6 This is a schematic diagram of the rear-mounted outrigger assembly;

[0034] Figure 7 is a schematic diagram of the housing structure;

[0035] As shown in the figure:

[0036]

[0037] DETAILED DESCRIPTION

[0038] The utility model is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the utility model, but do not limit the utility model in any form. It should be pointed out that for those of ordinary skill in the art, several changes and improvements can be made without departing from the concept of the utility model. These all belong to the protection scope of the utility model.

[0039] Example 1

[0040] Existing assembly technologies for aero-derivative gas turbine skids include: Figure 4-6 As shown, it is composed of a base 1, a cover 2, a front mounting leg assembly 3, an engine 4, a rear mounting leg assembly 5 and an engine output shaft 6, wherein the front mounting leg assembly 3 is further divided into a front left mounting leg 31 and a front right mounting leg 32, and the rear mounting leg assembly 5 is further divided into a rear left mounting leg assembly 51, a rear right mounting leg assembly 52 and a rear lower mounting leg assembly 53. The front mounting leg assembly 3 and the rear mounting leg assembly 5 stably mount the engine 4 on the base 1, the fasteners connect the cover 2 to the base 1, and the engine output shaft 6 is connected to the generator shaft. The cover 2 adopts an integrated design. If the engine 4 is to be replaced and installed, the pipelines and electrical lines attached to the cover 2 must be removed first, and then the cover 2 must be lifted, and then the engine 4 must be replaced and installed, and finally the cover 2 must be lifted back and reinstalled. The existing assembly technology is based on the fact that the engine is already in place and installed first. If the engine is not in place, the assembly work of the aeroderivative gas turbine generator set cannot be carried out at all. Therefore, this embodiment proposes an engine-free installation tool and method to eliminate the restriction of engine delivery time on the assembly work of the entire unit.

[0041] First, tooling is developed to simulate engine 4 and all its main external interfaces, guiding the assembly work of the aeroderivative gas turbine generator set to be carried out without an engine, and then the aeroderivative gas turbine cover 2 is designed to be split. When the engine 4 is in place, the engine 4 is hoisted from the cover top plate 22 into the cover 2 and replaced with the pre-installed tooling for installation. At this time, the assembly sequence of the entire unit is: install the tooling on the base 1 through the front and rear leg assemblies, drop the cover 2 on the base 1 and connect, connect the aeroderivative gas turbine pipelines, connect the aeroderivative gas turbine electrical connections, align the tooling with the generator, connect various auxiliary systems, remove the cover top plate 22 after the engine 4 is in place, replace the engine 4 with the tooling, and complete the assembly of the entire unit.

[0042] Specifically, Figure 1As shown, the installation tool of this embodiment includes: a main beam 8, a front connection assembly 11, a rear connection assembly 12, a centering dummy shaft 14, a centering support plate 15, a dial indicator 16 and an engine simulation pipeline 17; the front connection assembly 11, the rear connection assembly 12, the centering dummy shaft 14 and the engine simulation pipeline 17 are installed on the main beam 8, the centering support plate 15 is installed on the centering dummy shaft 14, and the dial indicator 16 is set on the centering support plate 15. The tool front support 9 and the tool rear support 10 are fixedly installed on the main beam 8 through the second fastening assembly 18, and the main beam 8 is supported by the tool front support 9 and the tool rear support 10.

[0043] like Figure 2-3 As shown, the front connection assembly 11 is arranged on both sides close to one end of the main beam 8, and the rear connection assembly 12 is arranged on the other end of the main beam 8. The front connection assembly 11 includes a front right connection member 111 and a front left connection member 112, and the front right connection member 111 and the front left connection member 112 are respectively located on both sides of the main beam 8; the rear connection assembly 12 includes: a rear right connection member 121, a rear lower connection member 122, a rear left connection member 123 and a mounting plate 124; the mounting plate 124 is installed on the main beam 8, and the rear right connection member 121, the rear lower connection member 122 and the rear left connection member 123 are installed on the mounting plate 124, and a reinforcing rib 13 is arranged between the mounting plate 124 and the main beam 8.

[0044] The gas turbine of this embodiment includes: a base 1, a casing 2, a front mounting leg assembly 3 and a rear mounting leg assembly 5; the front mounting leg assembly 3 and the rear mounting leg assembly 5 are mounted on the base 1, the casing 2 is fixedly mounted on the base 1 by a first fastening assembly 7, and the front mounting leg assembly 3 and the rear mounting leg assembly 5 are located in the casing 2. The front mounting leg assembly 3 includes a front left mounting leg 31 and a front right mounting leg 32, and the rear mounting leg assembly 5 includes a rear left mounting leg assembly 51, a rear right mounting leg assembly 52 and a rear lower mounting leg assembly 53.

[0045] The main beam 8 is placed in the cover 2, the front connecting assembly 11 is connected to the front mounting leg assembly 3, and the rear connecting assembly 12 is connected to the rear mounting leg assembly 5. The front left mounting leg 31 is connected to the front left connecting piece 112, the front right mounting leg 32 is connected to the front right connecting piece 111, the rear left mounting leg assembly 51 is connected to the rear left connecting piece 123, the rear right mounting leg assembly 52 is connected to the rear right connecting piece 121, and the rear lower mounting leg assembly 53 is connected to the rear lower connecting piece 122. The interface pipe in the cover 2 is connected to the engine simulation pipe 17, and the interface pipe includes a fuel pipe, an oil pipe and a gas pipe.

[0046] like Figure 7 As shown, the housing 2 includes: a housing body 21 and a housing top plate 22; the housing body 21 is fixedly mounted on the base 1, and the housing top plate 22 is detachably mounted on the housing body 21 by fasteners.

[0047] Example 2

[0048] Example 2 is a preferred example of Example 1.

[0049] like Figure 1-3 As shown, the tooling of this embodiment includes: a main beam 8, a tooling front support 9, a tooling rear support 10, a front connecting assembly 11, a front right connecting piece 111, a front left connecting piece 112, a rear connecting assembly 12, a rear right connecting piece 121, a rear lower connecting piece 122, a rear left connecting piece 123, a mounting plate 124, a reinforcing rib 13, a centering dummy shaft 14, a centering support plate 15, a dial indicator 16, an engine simulation pipeline 17 and a second fastening assembly 18. The tooling carries out the assembly work of the simulated engine from three aspects: first, the simulated engine 4 is assembled on the cover 2, namely, the front right connecting piece 111 and the front left connecting piece 112 simulate the front end installation interface of the engine 4, and complete the connection with the front left mounting leg 31 and the front right mounting leg 32; the rear right connecting piece 121, the rear lower connecting piece 122 and the rear left connecting piece 123 simulate the rear end installation interface of the engine 4, and complete the connection with the rear left mounting leg assembly 51, the rear right mounting leg assembly 52 and the rear lower mounting leg assembly 53; the second simulates the connection of the main interface pipelines of the engine 4, including the fuel pipeline, the oil pipeline and the gas pipeline, Figure 1 The engine simulation pipeline 17 shown in the middle only represents one of the main pipelines of the engine 4. The engine simulation pipeline 17 is connected to the main beam 8. Through all pipeline simulations, the connection of the main external joint pipelines of the engine 8 can be completed; the third simulates the centering installation of the engine 4 and the generator. The engine output shaft 6 is simulated by the centering dummy shaft 14. The centering dummy shaft 14 is threadedly connected to the main beam 8. A centering support plate 15 is connected to the end of the centering dummy shaft 14. Axial and radial dial indicators 16 are set on the centering support plate 15. The dial indicator 16 monitors the relative position relationship between the centering dummy shaft 14 and the generator shaft, and the centering installation is finally completed through adjustment.

[0050] The main beam 8 is the tooling base. The working front support 9 and the tooling rear support 10 are connected to the bottom of the main beam 8 through the second fastening assembly 18 to support the main beam 8. The front connecting assembly 11 is connected to the front two sides of the main beam 8 through fasteners, and is divided into a front right connecting piece 111 and a front left connecting piece 112, simulating the front leg installation interface of the aero-derivative gas turbine; the rear connecting assembly 12 is divided into a rear right connecting piece 121, a rear lower connecting piece 122, a rear left connecting piece 123, a mounting plate 124 and a reinforcing rib 13. The reinforcing rib 13 is welded to the main beam 8, and the mounting plate 124 is welded to the reinforcing rib 13. The reinforcement 13 is welded, and the rear right connector 121, the rear lower connector 122 and the rear left connector 123 are connected to the mounting plate 124 through fasteners, simulating the rear leg mounting interface of the aeroderivative gas turbine; the centering dummy shaft 14 simulates the engine output shaft 6 of the aeroderivative gas turbine, the centering support plate 15 is connected to the centering dummy shaft 14, and the dial indicator 16 is connected to the centering support plate 15, simulating the centering installation of the aeroderivative gas turbine and the generator; the engine simulation pipeline 17 simulates the main external pipeline interface of the aeroderivative gas turbine to ensure the assembly of the pipeline without an engine.

[0051] like Figure 7 As shown, the cover shell 2 of this embodiment has a split design, and the cover shell 2 is divided into a cover shell body 21 and a cover shell top plate 22, and the two are connected by fasteners. At this time, if the engine 4 needs to be replaced and installed, it is only necessary to remove the cover shell top plate 22, and the engine 4 can be lifted out and lifted in from the top of the cover shell 2, and at the same time, the removal and reinstallation of the pipelines and electrical lines attached to the cover shell 2 are eliminated, which greatly reduces the workload of replacing and installing the engine 4.

[0052] In one embodiment, the tooling is made of conventional profiles, which are easy to obtain and process. The tooling is a purely mechanical structural part and does not require regular maintenance.

[0053] The engine-free installation process of this embodiment is as follows:

[0054] After the tooling is in place, it is hoisted onto the base 1 of the gas turbine, and then the front connecting assembly 11 and the rear connecting assembly 12 of the tooling are respectively connected to the front mounting leg assembly 3 and the rear mounting leg assembly 5 of the gas turbine, and then the engine simulation pipe 17 of the tooling is connected to the interface pipe of the gas turbine; the centering dummy shaft 14 of the tooling is installed in alignment with the generator shaft through the dial indicator 16; then the cover 2 of the gas turbine is installed on the base 1, and the auxiliary system of the gas turbine unit is connected; when the engine 4 of the gas turbine is in place, the cover top plate 22 of the gas turbine cover 2 is removed, and the engine 4 is replaced with the tooling; then the remaining pipes and electrical equipment in the cover 2 are connected to the engine 4; finally, the cover top plate 22 of the cover 2 is reinstalled.

[0055] This embodiment first simulates the engine 4 through the tooling to ensure that all assembly work of the entire aircraft-derivative gas turbine generator set can be completed without the engine 4, and then the engine 4 and its tooling can be replaced and installed through the split design of the cover 2, and finally the engine-free installation technology is realized, which not only ensures the assembly progress of the project, but also has significant economic benefits. Compared with the engine 4, the tooling of this embodiment is small in size and occupies a small space in the cover 2, which in disguise increases the assembly space and is easy for personnel to operate; the tooling fully simulates the engine 4 from three dimensions: engine installation, engine external pipeline interface, and engine centering installation, to ensure that the unit assembly work can proceed smoothly without the engine; the cover 2 is designed to be split, and the replacement installation of the engine 4 and the tooling can be easily achieved through the disassembly and assembly of the cover top plate 22.

[0056] In the description of the present application, it should be understood that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0057] The above describes the specific embodiments of the present invention. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other at will.

Claims

1. An aeroderivative gas turbine engineless installation tool, characterized in that: include: A main beam (8), a front connecting assembly (11), a rear connecting assembly (12), a centering dummy shaft (14), a centering support plate (15), a dial indicator (16), and an engine simulation pipe (17); The main beam (8) is installed with a front connection assembly (11), a rear connection assembly (12), a centering dummy shaft (14) and an engine simulation pipe (17); the centering dummy shaft (14) is installed with a centering support plate (15); and a dial indicator (16) is arranged on the centering support plate (15).

2. The engineless installation tool for an aeroderivative gas turbine according to claim 1, characterized in that: The front connection assembly (11) is arranged on both sides close to one end of the main beam (8), and the rear connection assembly (12) is arranged at the other end of the main beam (8).

3. The engineless installation tool for an aeroderivative gas turbine according to claim 1, characterized in that: The front connection assembly (11) comprises a front right connection member (111) and a front left connection member (112), wherein the front right connection member (111) and the front left connection member (112) are respectively located on two sides of the main beam (8); The rear connection assembly (12) comprises: a rear right connection piece (121), a rear lower connection piece (122), a rear left connection piece (123) and a mounting plate (124); The mounting plate (124) is mounted on the main beam (8), and a rear right connecting piece (121), a rear lower connecting piece (122), and a rear left connecting piece (123) are mounted on the mounting plate (124).

4. The engineless installation tool for an aeroderivative gas turbine according to claim 3 is characterized by: A reinforcing rib (13) is provided between the mounting plate (124) and the main beam (8).

5. The engineless installation tool for an aeroderivative gas turbine according to claim 1, characterized in that: The tooling front support (9) and the tooling rear support (10) are fixedly mounted on the main beam (8) via a second fastening assembly (18), and the main beam (8) is supported by the tooling front support (9) and the tooling rear support (10).

6. A gas turbine using the aeroderivative gas turbine engine-free installation tooling as claimed in claim 3 or 4, characterized in that: include: A base (1), a cover (2), a front mounting leg assembly (3) and a rear mounting leg assembly (5); The front mounting leg assembly (3) and the rear mounting leg assembly (5) are mounted on the base (1), the cover shell (2) is fixedly mounted on the base (1) via a first fastening assembly (7), and the front mounting leg assembly (3) and the rear mounting leg assembly (5) are located inside the cover shell (2); The main beam (8) is placed in the cover shell (2), the front connecting assembly (11) is connected to the front mounting leg assembly (3), and the rear connecting assembly (12) is connected to the rear mounting leg assembly (5).

7. The gas turbine according to claim 6, characterized in that: The front mounting leg assembly (3) comprises a front left mounting leg (31) and a front right mounting leg (32), and the rear mounting leg assembly (5) comprises a rear left mounting leg assembly (51), a rear right mounting leg assembly (52) and a rear lower mounting leg assembly (53); The front left mounting leg (31) is connected to the front left connecting piece (112), the front right mounting leg (32) is connected to the front right connecting piece (111), the rear left mounting leg assembly (51) is connected to the rear left connecting piece (123), the rear right mounting leg assembly (52) is connected to the rear right connecting piece (121), and the rear lower mounting leg assembly (53) is connected to the rear lower connecting piece (122).

8. The gas turbine according to claim 6, characterized in that: The interface pipe in the housing (2) is connected to the engine simulation pipe (17), and the interface pipe comprises a fuel pipe, an oil lubrication pipe and a gas pipe.

9. The gas turbine according to claim 6, characterized in that: The housing (2) comprises: a housing body (21) and a housing top plate (22); The casing body (21) is fixedly mounted on the base (1), and the casing top plate (22) is detachably mounted on the casing body (21) via fasteners.

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