WO2015110224A1

WO2015110224A1 - Aligning method

Info

Publication number: WO2015110224A1
Application number: PCT/EP2014/077736
Authority: WO
Inventors: Dirk MÜLLER
Original assignee: Siemens Aktiengesellschaft
Priority date: 2014-01-27
Filing date: 2014-12-15
Publication date: 2015-07-30
Also published as: DE102014201391A1

Abstract

The invention relates to a method for aligning an outlet end of a tubular combustion chamber (5) mounted on a gas turbine burner (1) of a gas turbine arrangement relative to an inlet end of a tubular transfer channel (6), which is positioned in a housing (2) of the gas turbine arrangement and which conducts combustion gases exiting the combustion chamber (5) to a turbine of the gas turbine arrangement, said method having the following steps: a) securing a centering ring (10) to the outlet end of the combustion chamber (5), said centering ring (10) having at least one circumferential centering face (11) which can be inserted into the inlet end of the transfer channel (6), thereby radially centering the combustion chamber (5) and the transfer channel (6); b) pre-adjusting the transfer channel (6) in the region of the intended position of the transfer channel within the housing (2); c) introducing the gas turbine burner (1) into the housing (2); d) introducing the centering face (11) of the centering ring (10) into the inlet end of the transfer channel (6), the transfer channel (6) being moved into the centered position; e) securing the transfer channel (6) in the centered position; and f) securing the gas turbine burner (1).

Description

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The present invention relates to a method for aligning an outlet end of a tubular combustion chamber mounted on a gas turbine combustor of a gas turbine assembly to an inlet end of a tubular transition duct positioned in a housing of the gas turbine assembly that directs combustion gases exiting the combustor to a turbine of the gas turbine assembly.

Gas turbine assemblies are known in the art. They include a compressor, multiple gas turbine burners and a turbine. During operation, ambient air is compressed using the compressor and supplied to the gas turbine combustors, where the compressed air is mixed with fuel and the mixture is burned to produce combustion gases. The combustion gases leave the respective combustors of the gas turbine burners and are via transitional channels, each with the combustion chambers of the

Gas turbine burners are connected, led to the turbine, the blades are driven by the combustion gases rotating. In assembling a gas turbine assembly, the exhaust ends of the combustors of the gas turbine combustors must be inserted into the inlet ends of the associated transition ducts by which the exhaust ends of the combustors must be aligned with the inlet ends of the transition ducts. This alignment process is problematic due to the usually very large dimensions and the associated high weight of the components.

Based on this prior art, it is an object of the present invention to provide a method of the type mentioned, which is easy to carry out. To achieve this object, the present invention provides a method of the type mentioned above, comprising the steps:

a) attaching a centering ring at the outlet end of the combustion chamber, the centering ring having at least one circumferentially formed centering surface insertable into the inlet end of the transition duct to provide radial centering of the combustion chamber and transition duct;

b) pre-adjustment of the transitional channel in the region of its intended position within the housing;

c) inserting the gas turbine burner into the housing;

d) inserting the centering of the centering in the

Inlet end of the transition channel, wherein the transition channel is transferred to its centered position;

e) fixing the transition channel in the centered position; and

f) fixing the gas turbine burner.

Thanks to the use of a centering ring according to the invention, the outlet end of the combustion chamber and the inlet end of the transition channel can be aligned very accurately and without problems, whereby proper operation of the gas turbine arrangement can be ensured with little effort.

According to one embodiment of the method according to the invention, following step e) before the gas turbine burner is fixed in step f) the steps are carried out: g) retraction of the gas turbine burner until the centering surface of the centering ring comes out of engagement with the inlet end of the transition channel and the centering ring free is accessible;

h) disassembly of the centering ring from the outlet end of the

combustion chamber; and

i) introducing the outlet end of the combustion chamber into the inlet end of the transition channel. In this variant, so the centering ring is removed again and can be used again accordingly.

Alternatively, the gas turbine burner can also be fixed with the centering ring in step f), so that the centering ring remains in the arrangement.

According to one embodiment of the invention, the centering ring is made of a material whose melting temperature is below the operating temperature of the burner chamber, in particular of hard wax, so that it dissolves during operation.

Preferably, the centering ring is attached in step a) by means of a plug connection to the outlet end of the combustion chamber. Accordingly, the centering ring can be fixed in a simple manner without additional fastening means at the outlet end of the combustion chamber. Advantageously, the centering ring is provided with an annular groove which is designed such that the centering ring can be slidingly pushed onto the outlet end of the combustion chamber. As a result, a particularly simple construction of the centering ring is achieved.

Preferably, the steps b) and e), ie the pre-adjustment of the transitional channel in the region of its intended position within the housing and the fixing of the transitional channel in the centered position, using an adjusting and fixing device, with which the transition channel is attached to the housing ,

According to one embodiment of the method according to the invention, the outer circumference of the outlet end of the combustion chamber is provided with radially outwardly projecting spring elements, which come into clamping engagement with the inner circumference of the inlet end of the transitional channel in the intended state. correspond Accordingly, the outlet end of the combustion chamber is automatically fixed when inserted into the inlet end of the transition channel.

Further features and advantages of the present invention will become apparent from the following description of an embodiment of a method according to the invention with reference to the accompanying drawings. That's it

FIG. 1 shows a schematic sectional view showing a gas turbine burner of a gas turbine arrangement in the installed state;

Figure 2 is a schematic sectional view of the arrangement shown in Figure 1, showing the gas turbine burner in a first mounting position;

FIG. 3 shows a schematic sectional view of the arrangement shown in FIG. 1, which shows the gas turbine burner in a second assembly position, in which a centering ring is fastened to an outlet end of a combustion chamber of the gas turbine burner;

Figure 4 is an enlarged view of the designated in Figure 3 by the reference numeral IV section;

Figure 5 is a perspective view of the centering ring shown in Figures 3 and 4;

Figure 6 is a schematic sectional view of the arrangement shown in Figure 1, showing the gas turbine burner in a third mounting position, in which the inlet end of the combustion chamber of the gas turbine burner is held with centering ring inserted into the outlet end of a transitional channel.

Figure 7 is an enlarged view of the designated in Figure 6 by the reference numeral VII section; and FIG. 8 shows a schematic sectional view of the arrangement shown in FIG. 1, which shows the gas turbine burner in a fourth assembly position, in which the gas turbine burner with the centering ring held thereon is in a retracted position relative to the transition channel.

FIG. 1 shows a region of a gas turbine arrangement in which a gas turbine burner 1 is inserted into a housing 2 of the gas turbine arrangement. The gas turbine burner 1 is connected via a flange 3 with a connecting housing 4, which in turn is screwed to the housing 2. In alternative gas turbine arrangements, however, the flange 3 can also be fastened directly to the housing 2, that is, the connection housing 4 can be dispensed with. The gas turbine combustor 1 has a tubular combustion chamber 5, the outlet end of which is connected to an inlet end of a tubular transition channel positioned in the housing 2 of the gas turbine assembly

6 is connected, via an adjusting and fixing

7 is held on the housing 2. More specifically, the outlet end of the combustion chamber 5 is inserted into the inlet end of the transitional channel 6, wherein on the outer periphery of the outlet end of the combustion chamber 5 provided radially outwardly projecting spring elements 8 with the inner periphery of the inlet end of the transition channel 6 are clampingly engaged, whereby the outlet - End of the combustion chamber 5 is held centrally within the inlet end of the transition channel 6.

During operation of the gas turbine assembly, compressed ambient air and fuel are combusted in the gas turbine combustor 1, burned in the combustion chamber 5, and the combustion gases generated in this way are introduced into the transition duct and fed via the transition duct 6 to the turbine, where the combustion gases are the rotor of the turbine drive.

During assembly of the arrangement shown in Figure 1, the outlet end of the combustion chamber 5 and the inlet end of the transition channel 6 must be aligned with each other. According to According to one embodiment of such an alignment method according to the present invention, the steps explained below are carried out: In a first step, the transition channel 6 is pre-adjusted in the region of its intended position within the housing 2 using the adjusting and fixing device 7 according to FIG. The Vorjustage can be done for example by a loose tightening of adjusting and fixing screws of the adjusting and fixing device 7, not shown in the figures. Further, the gas turbine combustor 1 is partially inserted into the housing 2 through a through-hole 9 extending through the housing 2 and the connection housing 4 such that a clearance a between the outlet of the combustion chamber 5 and the inlet end of the transitional passage 6 is sized is that the outlet end of the combustion chamber 5 is still accessible.

In a further step, as shown in Figure 3, a centering ring 10 is attached to the outlet end of the combustion chamber 5, wherein the centering ring 10 has a circumferentially formed centering surface 11, which in the inlet end of the transition channel 6 to bring about a radial centering of the combustion chamber and transition channel 6 can be inserted. The fastening of the centering ring 10 at the outlet end of the combustion chamber 5 takes place here by means of a plug connection. For this purpose, the centering ring is provided with an annular groove 12, which is formed such that the centering ring 10 can be slidingly pushed onto the outlet end of the combustion chamber 5, as shown in the enlarged view of FIG.

In a further step, the centering surface 11 of the centering ring 10 is inserted into the inlet end of the transition channel 6, as shown in Figures 6 and 7, wherein the transition channel 6 is transferred to its centered position. Subsequently, the transition channel 6 in this centered position by means of the adjusting and fixing device 7 fixed by the aforementioned adjustment and fixing screws are fully tightened.

Subsequently, the gas turbine burner 1, as shown in Figure 8, partially withdrawn by a dimension b in the axial direction until the centering surface 11 of the centering ring 10 comes out of engagement with the inlet end of the transition channel 6 and the centering ring 10 is freely accessible again. The dimension b can correspond to the dimension a according to FIG. In this position, the centering ring 10 is then removed from the outlet end of the combustion chamber 5.

In a subsequent step, the outlet end of the combustion chamber 5 is inserted into the inlet end of the transition channel 6 until the spring elements 8 arranged on the outer circumference of the outlet end of the combustion chamber 5 engage with the inner circumference of the inlet end of the transition channel 6. Further, the gas turbine combustor 1 is fixed by the flange 3 is bolted to the connection housing 4. Thus, the arrangement shown in Figure 1 is produced.

Thanks to the use of a centering ring 10 according to the invention, the outlet end of the combustion chamber 5 and the inlet end of the transition channel 6 can be aligned very precisely and without problems, whereby proper operation of the gas turbine arrangement can be ensured with little effort.

In an alternative embodiment of the method according to the invention, the gas turbine burner 1 can also be fixed directly after fixing the transition channel 6 in the central position, so that the intermediate steps are eliminated. Accordingly, the centering ring 10 remains in the arrangement. According to a variant of the centering ring 10 may be made of a material whose melting temperature is lower than the operating temperature to which the centering ring 10 is exposed during operation. Accordingly, the centering ring 10 dissolves under operating conditions. Although the invention has been further illustrated and described in detail by the preferred embodiment, the invention is not limited by the disclosed examples, and other variations can be derived therefrom by those skilled in the art without departing from the scope of the invention.

Claims

claims

A method of aligning an outlet end of a tubular combustion chamber (5) mounted on a gas turbine combustor (1) of a gas turbine assembly to an inlet end of a tubular transition duct (6) positioned in a housing (2) of the gas turbine assembly exiting the combustion chamber (5) Directing combustion gases to a turbine of the gas turbine engine assembly, the method comprising the steps of:

a) attaching a centering ring (10) at the outlet end of

Combustion chamber (5), wherein the centering ring (10) has at least one circumferentially formed centering surface (11) in the inlet end of the transition channel (6) below

Inducing a radial centering of the combustion chamber (5) and transition channel (6) can be inserted;

b) pre-adjustment of the transitional channel (6) in the region of its intended position within the housing (2);

c) introducing the gas turbine burner (1) into the housing (2); d) inserting the centering surface (11) of the centering ring (10) in the inlet end of the transition channel (6), wherein the transition channel (6) is transferred to its centered position;

e) fixing the transition channel (6) in the centered position; and

f) fixing the gas turbine burner (1).

2. The method according to claim 1,

in which the steps are carried out following step e) before the gas turbine burner (1) is fixed in step f):

- Retracting the gas turbine burner (1) until the centering surface (11) of the centering ring (10) comes out of engagement with the inlet end of the transition channel (6) and the centering ring (10) is freely accessible;

- Disassembly of the centering ring (10) from the outlet end of the combustion chamber (5); and

- Introducing the outlet end of the combustion chamber (5) in the inlet end of the transition channel (6).

3. The method according to claim 1,

in which the gas turbine burner (1) is fixed with inserted centering ring (10) in step f).

4. The method according to claim 3,

in which the centering ring (10) is made of a material whose melting temperature is below the operating temperature of the combustion chamber (5), in particular of hard wax.

5. The method according to any one of the preceding claims, wherein the centering ring (10) in step a) by means of a plug connection at the outlet end of the combustion chamber (5) is fastened.

6. The method according to claim 5,

in which the centering ring (10) is provided with an annular groove (12) which is designed in such a way that the centering ring (10) can be slidingly pushed onto the outlet end of the combustion chamber (5).

7. The method according to any one of the preceding claims, wherein the steps b) and e) are carried out using an adjusting and fixing device (7), with which the transition channel (6) is fixed to the housing (2).

8. The method according to any one of the preceding claims, wherein the outer circumference of the outlet end of the combustion chamber (5) with radially outwardly projecting spring elements (8) is provided, which come in the proper condition with the inner periphery of the inlet end of the transition channel (6) by clamping.