WO2015158506A1

WO2015158506A1 - Method for installing a seal between a gas-turbine tube combustion chamber and a transition piece

Info

Publication number: WO2015158506A1
Application number: PCT/EP2015/056324
Authority: WO
Inventors: Thorsten Drogan; Fabian Niederbremer
Original assignee: Siemens Aktiengesellschaft
Priority date: 2014-04-14
Filing date: 2015-03-25
Publication date: 2015-10-22
Also published as: EP2933562A1

Abstract

The invention relates to a method for assembling a gas-turbine burner assembly, comprising: a gas-turbine burner (1), which has a tubular combustion chamber (5); a tubular transition channel (6), which conducts combustion gases exiting the combustion chamber (5) to a turbine of the gas-turbine assembly, wherein an outlet end of the combustion chamber (5) leads into an inlet end of the transition channel (6) and is oriented concentrically to the inlet end of the transition channel in the intended state; and a resilient seal device, which seals an annular gap present between the outlet end of the combustion chamber (5) and the inlet end of the transition channel (6) in the intended state; wherein the method comprises the following steps: a) arranging the seal device on the outer circumference of the outlet end of the combustion chamber (5); b) at least partially filling at least one cavity, which is present between the seal device and the combustion chamber (5) and which defines the spring deflection of the seal device, with a filling material (12), which supports the seal device and the flash point of which lies below the operating temperature of the gas-turbine burner (1) in the region of the seal device; c) inserting the outlet end of the combustion chamber (5) into the inlet end of the transition channel (6), the transition channel being arranged in a housing of the gas-turbine assembly; and d) fastening the transition channel (6) and the combustion chamber (5).

Description

description

METHOD FOR ASSEMBLING A SEAL BETWEEN A GAS TUBE BURNER CHAMBER AND A TRANSITION PIECE

The present invention relates to a method for assembling a gas turbine burner arrangement with a gas turbine burner, which has a tubular combustion chamber, a tubular transition channel, the combustion chamber leaving combustion Ver ^¬ combustion gases to a turbine of the gas turbine arrangement passes, wherein an outlet end of the combustion chamber in bestimmungsge ^¬ MAESSEN state ^¬ inserted into an inlet end of the transition duct and concentrically aligned thereto, and a resiliently formed sealing means in a predetermined state, between the outlet end of the

Combustion chamber and the inlet end of the transitional ^channel existing ^¬ ring gap seals. Furthermore, the present invention relates ^¬ a gas turbine combustor.

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 ^¬ burners in which mixed the compressed air with fuel ^¬ substance and the mixture to produce combustion gases is burned. The combustion gases leave the combustion chambers of the gas turbine burners and are passed through transition channels, which are each connected to the combustion chambers of Gasturbi ^¬ nenbrenner to the turbine, the blades are driven in rotation by the combustion gases.

During assembly of a gas turbine burner arrangement of the type mentioned in the outlet end of the combustors of the gas turbine combustor needs to be introduced into the inlet end of the associated About ^¬ transition duct, which is already arranged in a housing of the gas turbine arrangement. To ensure proper operation of the gas turbine ^burner arrangement, the outlet end of the combustion chamber and the inlet Align the transitional channel concentrically. In the case of not sufficiently concentric alignment, there is also the risk that the sealing device will be damaged during operation of the gas turbine arrangement, which should be avoided. In this context, the use of an alignment device is known, which is introduced in a first step instead of a gas turbine burner in the housing of a Gasturb ^¬ binenanordnung and secured thereto. The alignment device comprises a dial gauge, by means of which then within a predetermined tolerance range ^¬ semi aligned, the inlet end of the associated transition duct who can ^¬. After alignment, the transition channel is fixed in the aligned position and the alignment removed again, after which the gas turbine burner mounted under the introduction of the outlet end of its combustion chamber in the inlet end of the aligned transitional ^{channel ¬} who can. A disadvantage of the use of such an alignment ^{¬ device} is that this is associated with much effort and high costs. In addition, proper alignment due to the added tolerances can not always be guaranteed, so that proper operation can not be guaranteed and damage to the sealing device can not be safely ruled out. Based on this prior art, it is an object of the present invention to provide an alternative method for assembling a gas turbine burner assembly of the type mentioned, which can be carried out easily and inexpensively and prevents installation-related damage to the sealing device.

To achieve this object, the present invention provides a method of the type mentioned above, comprising the steps:

a) arranging the sealing device on the outer circumference of

Outlet end of the combustion chamber;

b) at least partially filling at least one existing between the sealing device and the combustion chamber, Defining the travel of the sealing device

Cavity with a sealing device supporting filler material whose flash point is below the loading ^¬ operating temperature of the gas turbine burner in the region of the sealing device; and

c) inserting the outlet end of the combustion chamber into the inlet end of the transition channel arranged in a housing of the gas turbine arrangement and

d) fixing the transition duct and the combustion chamber.

The provision of a supporting filler in step b) ensures that the sealing device can only be compressed to a defined extent during insertion of the outlet end of the combustion chamber into the inlet end of an associated transition channel, as further compression by the filler material is prevented. In this way a concen ^¬ generic orientation of the combustion chamber and transfer channel is automatically ensured without additional alignment device during the insertion of the outlet end of the combustion chamber into the inlet end of the transition duct. Accordingly, the installation of a gas turbine burner can be performed quickly, easily and inexpensively. After the insertion process, only the transition duct and the gas turbine burner still need to be fixed to the housing. During operation of the gas turbine nena arrangement of the filler material melts and gives you ^¬ processing device again completely free, so this system ^¬ peraturbedingte movements between the outlet end of the

Combustion chamber and the inlet end of the transition channel can compensate ^¬ chen.

The sealing device according to an embodiment of the method according to the invention before the implementation of Schrit tes b) biased ^¬ reducing its outer diameter ^¬ . In this way, the outer diameter of the cavity, which is filled in step b) with the filling material, and thus the accuracy of the coaxial alignment is ^¬ sets. For biasing the sealing device, a clamping ring is preferably used. Such a clamping ring is placed around the sealing device in order then to introduce the filling material in the pretensioned state of the sealing device into the at least one cavity. The clamping ring can also be mounted during transport of the gas turbine burner lead ^¬ ben to protect the sealing device from external damage. Only shortly before the installation of the gas turbine burner, the clamping ring must be removed.

Advantageously, the filler material is a wax, a polymer or a resin. For example, natural waxes, synthetic waxes, natural resins, synthetic resins or the like can be used. When selecting the filler material, care must be taken to ensure that it does not adversely affect the operation of the gas turbine arrangement in the molten state.

According to one embodiment of the method according to the invention, the sealing device has spring elements which protrude radially outwards from the outer surface of the combustion chamber and in the proper state are in sealing engagement with the inner circumference of the inlet end of the transitional channel. With derar ^¬ term spring elements a simple construction is achieved.

To achieve the aforementioned object of the products contained ^¬ constricting invention further provides a gas turbine combustor, comprising a tubular combustion chamber having an outlet end, at its outer periphery a resiliently designed Dichtungsein- direction is arranged in the intended state a between the outlet of the combustion chamber and an inlet end a sealing ring arranged in a housing of a gas turbine arrangement seals annular gap, characterized in that at least one existing between the sealing device and the combustion chamber, the

Spring cavity of the sealing device defining cavity is at least partially filled with a sealing device abstüt ^¬ zenden filling material whose flash point below the operating temperature of the gas turbine burner is in the region of the sealing device.

The sealing means preferably comprises spring elements comprises up, are projecting from the outer surface of the combustion chamber radially from ^¬ Windwärts and in the predetermined state with the inner circumference of the inlet end of the transition duct sealingly engaged. The spring elements are advantageously arranged on a spring element ring held on the outer circumference of the combustion chamber. In this way, a simple structure is achieved.

The filler material, as previously described, is preferably a wax, a polymer or a resin.

Further features and advantages will become apparent from the following description of an embodiment of a gas turbine combustor according to the invention with reference to the accompanying drawings. This is / are

Figure 1 is a schematic cross-sectional view of a Gastur ^¬ binenanordnung showing a gas turbine burner and a transition duct in the assembled state;

Figures 2 to 5 are schematic partial cross sectional views of an outlet of a combustion chamber of the dargestell ^¬ th in Figure 1 the gas turbine combustor, the basis of which a filling of a see be- an opening provided at the outlet end of the combustion chamber sealing means and the outer surface of the combustion chamber existing annular cavity with a filler material be ^¬ written is; and Figs 6 to 8 are schematic partial sectional perspective ^¬ views showing various degrees of filling of the existing between the like ^¬ processing device and the outer surface of the combustion chamber cavity with a filler material. 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. At al ^¬ ternatives gas turbine arrangements of the flange 3 but can also be attached directly to the housing 2, thus dispenses with the connector housing. 4 The Gasturbinenbren- ner 1 has a tubular combustion chamber 5, the capacity utilization ^¬ broadcasting with an inlet end of a positioned in the housing 2 of the gas turbine arrangement ^¬ tubular transition duct

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 transition ^¬ channel 6, wherein between the combustion chamber 5 and the transition channel 6, a sealing device is arranged, which provided by on the outer circumference of the outlet end of the combustion chamber 5 on a spring element ring, radially outward projecting spring elements 8 is formed, which are sealingly engaged with the inner ^¬ circumference of the inlet end of the transition channel 6. On the one hand, the spring elements 8 serve to seal the annular space existing between the combustion chamber 5 and the transition ^channel 6. On the other hand, they compensate for temperature-related movements between the combustion chamber 5 and the transition duct 6.

During operation of the gas turbine arrangement in the gas turbine combustor 6 compressed ambient air and fuel are mixed fuel, burned in the combustion chamber 5 and introduced generated in this manner the combustion gases in the Übergangska ^¬ nal 6 and supplied via the transfer channel 6 of the turbine where the combustion gases the Driven rotor of the turbine ^¬ .

In order to assemble the arrangement shown in FIG. 1, in a first step the transition channel 6 is made using the adjusting and fixing device 7 in the region of its well-adjusted position within the housing 2 roughly pre-adjusted. The Vorjustage can be done for example by a lo ^¬ ckeres tightening adjustment and fixing screws 9 of the adjusting and fixing device 7. In a further step, the gas turbine burner 1 by a through the housing 2 and the connecting housing 4 extending

Through opening 10 is inserted into the housing 2, wherein the outlet end of the combustion chamber 5 in the intake end of the passageway 6 ^¬ te with partial compression of the Federelemen- is inserted. 8 Here, the inlet end of the

Transition channel 6, if necessary, positioned manually with respect to the outlet end of the combustion chamber 5, so as to allow the insertion of the outlet end of the combustion chamber 5 in the inlet end of the transition channel 6. In a further step, the adjusting and Fixierschrau ^¬ Ben 9 are tightened to fix the inlet end of the transition channel 6. Furthermore, the gas turbine burner 1 is screwed to the connection housing 4. In order to ensure that the outlet end of the combustion chamber 5 and the inlet end of the transition duct 6 during the troduction ^¬ Rens be properly aligned coaxially with each other, the gas turbine combustor 1 is in advance as described below prepared as described with reference to Figures 2 to 8:

FIG. 2 shows the outlet end of the combustion chamber 5 in a state in which no external forces act on the spring elements 8. Starting from the state shown in Figure 2, the spring elements 8 are biased to reduce its outer diameter such that the existing between the combustion ^¬ chamber 5 and the spring elements 8 annular cavity has a predetermined outer diameter. For this purpose, starting from the free end of the combustion chamber 5 a

Clamping ring 11 pushed with a correspondingly selected inner diameter, as shown in Figure 3. In a ^further step, the annular cavity between the spring elements 8 and the outer surface of the combustion chamber 5, which in the prestressed state according to FIG. represents, as shown in Figure 4 filled with a supporting Füll ^¬ material 12 whose flame temperature is below the operating temperature of the gas turbine combustor 1 in the region of the spring elements 8. The filler material 12 may be, for example, a wax, a polymer or a resin, to name just a few examples.

After curing of the filling material 12, the clamping ring 11 is withdrawn again, so that the spring elements 8 move away from the filling material 12. This results in a gap 13 between the spring elements 8 and the filling material 12, as shown in FIG.

FIGS. 6 to 8 show different degrees of filling of the filling material 12 in the axial direction.

According to Figure 6, a low degree of filling is selected, in the zwi ^¬ tween the filler material 12 and a ring stop 14 with L-shaped cross-section, which limits the radial

Inward movement of the spring elements 8 is used, an annular gap 15 remains. Such a low degree of filling is characterized by a small contact surface between the spring elements 8 and the filling material 12, by a predetermined Biegebeanspru ^¬ chung on the spring elements during insertion into the inlet end of the transition channel 6 and by the possibility of axial movement of the filler material 12.

According to Figure 7, the degree of filling is chosen such that between the filler material 12 and the ring stop 14 no annular gap is no longer present. In this medium degree of filling is the

Contact surface between the spring elements 8 and the filler material 12 is greater and the bending stress of the spring elements during assembly less than in the Figure 6 Darge ^¬ presented low degree of filling. Furthermore, only a slight axial movement of the filler 12 is allowed. In addition, more wax is needed than in the variant described above in this average degree of filling. According to Figure 8, the degree of filling of the filler material 12 is chosen so high that the ring stop 14 is completely embedded in the filling ^¬ material 12. At this high degree of filling, the largest contact area between the spring elements 8 and the filling material 12 is achieved. An axial movement of the filling ^¬ material 12 is almost completely prevented, since the ring stop 14 prevents such. Furthermore, the spring elements 8 experience no bending stress during assembly. The disadvantage, however, is that in this variant more filler 12 is needed.

The essential advantage associated with filling the annular cavity between the spring elements 8 and the outer surface of the combustion chamber 5 with a filling material 12 supporting the spring elements 8 is that upon insertion of the outlet end of the combustion chamber 5 into the inlet end of the transitional channel 6 automatically an accurate coaxial alignment of combustion chamber 5 and transition channel 6 takes place, since a compression of the spring elements 8 beyond the filler material is not possible. Accordingly, the assembly of the gas turbine burner 1 is fast, simple and prob ^¬ lemlos feasible without separate alignment devices. The accuracy of the coaxial alignment can be adjusted by suitable adjustment of the outer diameter of the filling material to be filled with the cavity cavity in the context of Vorspan ^¬ nens and by a suitable choice of the filling height of the filler material.

During operation, the filling material melts, so that the proper functioning of the sealing device is not impaired by the filling material.

Although the invention in detail by the preferred embodiment has been illustrated and described in detail, the invention is not limited ^¬ by the disclosed examples and other variations can be derived therefrom by the skilled artisan without departing from the scope of the invention.

Claims

claims

A method of assembling a gas turbine combustor assembly with a gas turbine combustor (1) having a tubular one

Combustion chamber (5), a tubular transition channel (6), the combustion chamber (5) leaving combustion gases to a turbine of the gas turbine arrangement, wherein an outlet end of the combustion chamber (5) inserted in the intended state in an inlet end of the transition channel (6) and kon ^¬ is aligned centrally to this, and a resiliently ^¬ formed sealing ^device which seals in the normal state between the outlet end of the combustion chamber (5) and the inlet end of the transition channel (6) existing ring ^¬ gap, the method comprising the steps of: a ) Arranging the sealing device on the outer circumference of the

Outlet end of the combustion chamber (5);

b) at least partially filling at least one between the sealing device and the combustion chamber (5) existing, the spring travel of the sealing device defining cavity with a sealing device supporting Füllwerkstoff (12) whose flash point below the operating temperature of the gas turbine burner (1) in Be ^¬ rich the sealing device lies; and

c) inserting the outlet end of the combustion chamber (5) in the inlet end of which is arranged in a housing of the Gasturbinenanord ^¬ voltage transition duct (6) and

d) fixing the transition channel (6) and the combustion chamber

(5).

2. The method according to claim 1, characterized in that the sealing device is biased before performing step b) to reduce its outer diameter.

3. The method according to claim 2, characterized in that for biasing the sealing device, a clamping ring (11) is used.

4. The method according to any one of the preceding claims, characterized in that it is the filler material (12) is a wax, a polymer or a resin.

5. The method according to any one of the preceding claims, characterized in that the sealing means Federele ^¬ elements (8) which protrude radially outwardly from the outer surface of the combustion chamber (5) and in the proper state with the inner circumference of the inlet end of the transition channel (6 ) are sealingly engaged.

6. gas turbine burner (1) having a tubular combustion chamber (5) having an outlet end, on whose outer circumference a resiliently formed sealing device is arranged, which in the normal state a between the

Sealing end of the combustion chamber (5) and an inlet end of an arranged in a housing of a gas turbine arrangement transition duct (6) sealing annular gap, characterized in that at least one between the sealing device and the combustion chamber (5) existing, the spring travel of the sealing device defining cavity at least is partially filled with a filler material (12) supporting the sealing device, the flash point of which lies below the operating temperature of the gas turbine burner (1) in the region of the sealing device.

7. gas turbine burner (1) according to claim 6, characterized in that the sealing means comprises spring elements (8) projecting radially outwardly from the outer surface of the combustion chamber (5) and in the proper condition with the inner circumference of the inlet end of the transitional channel (6) sealingly in Are engaged.

8. gas turbine burner (1) according to claim 7, characterized in that the spring elements (8) are arranged on a on the outer circumference of the combustion chamber (5) held spring element ring.

9. gas turbine burner (1) according to one of claims 6 to 8, characterized in that it is the filler material (12) is a wax, a polymer or a resin.