ES2346159T3 - GAS TURBINE PROVISION. - Google Patents

Abstract

Gas turbine arrangement comprising: a conduit (1), of annular cross section, for transporting combustion gases; located in the duct (1), turbine blades (3) to be driven by the flue gases; a diffuser (5), annularly, to diffuse the combustion gases following its conduit (1) through the turbine blades (3); and a manifold (7) for collecting the flue gases diffused by the diffuser (5), the manifold (7) comprising an annular main part (9), and, located in a position around the annular main part (9), a neck outlet (11), in which during the use of the gas turbine arrangement, the combustion gases collected by the manifold (7) are transported around the annular main part (9) of the manifold (7) in opposite directions until reaching the outlet (11) of the collector neck (7) moving in opposite directions, characterized in that the outlet of the neck (11) of the collector (7) includes a dividing device (19) whereby the flows in opposite direction at the neck outlet (11) are kept substantially separated, in which the turbine blades (3) rotate around a central line (A) of the gas turbine arrangement, and the dividing device (19) runs parallel to the center line (A), and extends radially te from the central line (A), in which the diffuser (5) has a mouth (35) whereby the flue gases leave the diffuser (5) and enter the manifold (7), the device (19) of division comprises a first part (37) that extends over the mouth (35) and a second part (39) that extends towards one side of the mouth (35), and the second part (39) extends radially inwards to a position (41) closer to the center line (A) than the mouth (35).

Description

Gas turbine arrangement.

The present invention relates to a gas turbine arrangement.

More particularly, the present invention is refers to a gas turbine arrangement comprising: a conduit, annular cross section, for transporting gases from combustion; located in the duct, turbine blades that are going to actuated by combustion gases; a diffuser, annular, to diffuse the flue gases following its conduit to through the turbine blades; and a collector to collect the flue gases diffused by the diffuser, comprising the collector an annular main part, and, located in a position around the main annular part, a neck outlet, while using the gas turbine arrangement, transporting the combustion gases collected by the collector around the main annular part of the collector in opposite directions until reach the exit of the collector neck by moving in opposite directions.

A gas turbine arrangement of this type known is disclosed in document US3120374 and also shown in figures 1 to 4 of the attached drawings. Other Prior art arrangement is disclosed in the document JP 54064204. Figure 1 is a perspective view, sectioned of so that it shows the interior, of the arrangement, figure 2 is a longitudinal partial cross section of the arrangement, the Figure 3 is a schematic diagram illustrating the conduit of flue gases through the arrangement, and Figure 4 is a cross section on line IV-IV of the figure 3.

Referring to figures 1 to 4, the gas turbine arrangement comprises: a duct 1, of section transverse annular, to transport flue gases; located in the duct 1, turbine blades 3 to be operated by the Combustion gases; a diffuser 5, annularly, to diffuse flue gases following its conduit through the blades 3 turbine; and a manifold 7 to collect combustion gases diffused by the diffuser 5, the manifold 7 comprising a part 9 annular main, and, located in a position around the main ring part 9, a neck outlet 11.

During the use of the turbine arrangement of gas, combustion gases travel along the duct 1, drive the turbine blades 3, are diffused by the diffuser 5, and they are collected by the collector 7. The combustion gases, when leaving the diffuser 5, forms 7 flows 13a, 13b inside the manifold turbulent in the opposite direction first and second, see figure 4. These turbulent flows 13a, 13b are formed because the flue gas flow separates on flange 15 of diffuser protection 5, and wrapping up, see the arrows 17 in figure 3. The flow is then transported around the main annular part 9 of the collector 7, forming the flows 13a, 13b turbulent in the first and second opposite directions. These flows 13a, 13b are located at the outlet 11 of the upper neck of the manifold 7 moving in opposite directions.

The combustion gas flow separation on the protection flange 15, and the encounter of the flows 13a, 13b turbulent at the 11th neck exit, result in the production of an important entropy in the flow. This goes in detriment to the efficiency of the gas turbine arrangement.

According to the present invention a gas turbine arrangement having the characteristics according to claim 1 comprising: a duct, of section transverse annular, to transport flue gases; located in the duct, turbine blades that are to be driven by gases of combustion; a diffuser, annularly, to diffuse the gases of combustion following its conduit through the blades of turbine; and a collector to collect combustion gases diffused by the diffuser, the collector comprising a part main ring, and, located in a position around the part main ring, a neck outlet, in which during the use of the gas turbine arrangement, the combustion gases collected by the collector they are transported around the main part cancel the collector in opposite directions until reaching the exit of collector neck moving in opposite directions, characterized in that the collector neck outlet includes a dividing device by which the flows in direction opposite at the neck outlet remain substantially separated, in which the turbine blades revolve around a center line of the gas turbine arrangement, and the device of division runs parallel to the center line, and extends radially from the center line, in which the diffuser has a mouth whereby the flue gases leave the diffuser and enter the manifold, the dividing device it comprises a first part that extends over the mouth and a second part that extends to one side of the mouth, and the second part extends radially inward to a position closer to the center line than the mouth.

In a provision according to the preceding paragraph, it is better than the side of the first part that is addressed radially inward increase in distance from the center line as the distance from the second part increases.

In an arrangement according to any one of the two previous paragraphs, it is preferable that the device Division comprise a flat plate.

In an arrangement according to any one of the three previous paragraphs, it is preferable that the diffuser has a curved protection flange by which flue gases they leave the diffuser and enter the collector, the flange of protection has an extension that serves to increase the pressure recovery in the gas turbine arrangement, and the extension comprises a flat flange extension that is generally flat and forms a discontinuity with the curved protection flange.

Alternatively to the arrangement according to previous paragraph, it is preferable that the diffuser has a flange of curved protection whereby flue gases leave the diffuser and enter the collector, the protection flange has a extension that serves to increase pressure recovery in the gas turbine arrangement, and the extension comprises a spiral flange extension that continues or extends the curvature of the curved protection flange forming a spiral.

The invention will now be described, by way of example, with reference to the accompanying drawings, in the
that:

Figure 1, to which reference has already been made, it is a perspective view, sectioned so that it shows the inside, of a known gas turbine arrangement;

Figure 2, which has also been done already reference, is a longitudinal partial cross section of the arrangement of figure 1;

Figure 3, which has also been done already reference, is a schematic diagram illustrating the conduit of flue gases through the arrangement of figure 1;

Figure 4, which has also been done already reference, is a cross section on the line IV-IV of Figure 3;

Figure 5 is a perspective view, sectioned so that it reveals the interior, of an arrangement of gas turbine according to the present invention;

Figure 6 is a partial cross section longitudinal of the arrangement of figure 5;

Figure 7 is a schematic diagram that illustrates the flue gas duct through the arrangement of figure 5;

Figure 8 is a cross section on the line VIII-VIII of Figure 7;

Figure 9 illustrates in more detail the shape and the location of a divider plate in the arrangement of the figure 5;

Figure 10 illustrates divider plates alternatives to the divider plate of figure 9;

Figure 11 illustrates possible extensions to a protective flange of the arrangement of figure 5;

Figures 12, 13 and 14 illustrate, respectively, a flow of flue gases in three gas turbine arrangements;

Figures 15, 16 and 17 are plan views corresponding, respectively, to figures 12, 13 and 14;

Figures 18, 19 and 20 are side views corresponding, respectively, to figures 12, 13 and 14;

Figures 21 and 22 are perspective views corresponding, respectively, to figures 13 and 14; Y

Figure 23 illustrates an alternative form of a device of division to the flat plates of the figures previous.

In figures 5 to 23, the same elements as they appear in figures 1 to 4 are called with the same numbers reference.

Referring to figures 5 to 8, the arrangement of figures 5 to 8 is the same as that of figures 1  to 4 with the exception that manifold neck outlet 11 includes a dividing device in the form of a plate 19 divider by which the turbulent flows 13a, 13b in opposite direction at neck exit 11 remain substantially separated, ie divider plate 19 isolates the 13a, 13b turbulent flows from each other. The Divider Plate 19 runs parallel to the central line A of the arrangement of gas turbine, and extends radially from line A central.

By preventing the turbulent 13a, 13b flows from find, entropy production is reduced in the flow of flue gases through the gas turbine arrangement, thereby improving the effectiveness of the provision. The plate 19 divider has the advantage that it is simple in its design, and can be retrofitted in gas turbine arrangement manifolds current.

Figure 9 illustrates the shape and location precise of the divider plate 19 in the arrangement of figures 5 to 8. The diffuser 5 has a mouth 35 by means of which the gases of combustion leave diffuser 5 and enter manifold 7. The divider plate 19 comprises a first part 37 which extends over the mouth 35 and a second part 39 extending towards one side of the mouth 35. In Figure 9 it can be seen that the second part 39 extends radially inward to a position 41 closer to the center line A than the mouth 35. It can also be seen in Figure 9 that the 43 side of the first part 37 that goes radially inward increases progressively in distance from the center A line as increase the distance from the second part 39.

Figure 10 illustrates the precise form of three plates 21, 23, 25 alternative dividers. It should be noted that the last two plates (23,25) alternative dividers do not enter of the scope of the claims. Plate 21 is the same as plate 19 except that the side 45 of the plate 21 corresponding to the side 43 of the plate 19 remains at a constant distance from the central line A. Plate 23 can be derived from plate 21 removing the part of the plate 21 that is radially closer to center line A than side 45 of plate 21. Plate 25 can derive from the plate 23 eliminating a radially internal part additional plate 23. It should be noted that, in the case of two plates 23, 25, the sides 47 of the plates 23, 25 which are directed radially inward they remain at a constant distance from the central A line. It should also be noted that sides 47 are radially farther from the center line A than the mouth 35 of the diffuser 5.

Figure 11 illustrates two possible extensions 29, 31 to diffuser protection flange 15 of the arrangement of Figures 5 to 8. Extensions 29, 31 serve to increase the pressure recovery in the gas turbine arrangement, about and above that obtained using a divider plate alone. The extensions 29, 31 diffuse the flow of flue gases from a more controlled way, weakening the whirlpools formed in the manifold 7. Extension 29 comprises a flange extension flat, and is generally flat, and forms a discontinuity with protection flange 15. Extension 31 comprises a spiral flange extension, and continue or extend the curvature of the protection flange 15 forming a spiral.

Figure 12 illustrates a gas flow of combustion in diffuser 5 and manifold 7 of the arrangement of known gas turbine of figures 1 to 4. It should be noted that strong whirlpools occur in the main annular part 9 of the collector 7, and the mixture of flows 13a, 13b occurs turbulent at the outlet 11 of the collector neck 7.

Figure 13 illustrates a gas flow of combustion in diffuser 5 and manifold 7 of an arrangement of gas turbine that includes a divider plate 19 alone, that is to say does not include an extension 29, 31 to the protection flange 15 such as shown in figure 11. It should be noted that they follow producing strong whirlpools in the main ring part 9 of manifold 7, but a mixture of flows 13a, 13b does not occur turbulent at the outlet 11 of the collector neck 7.

Figure 14 illustrates a gas flow of combustion in diffuser 5 and manifold 7 of an arrangement of gas turbine that includes a divider plate 19 and an extension 29 of flat flange. It should be noted that only weak occur whirlpools in the main annular part 9 of the manifold 7, and, in addition, there is no mixture of turbulent flows 13a, 13b in the outlet 11 of the collector neck 7.

Figures 15, 16 and 17 are views taken from above in figures 12, 13 and 14 respectively. Plate 19 divider can be seen in figures 16 and 17. Extension 29 of flat flange can be seen in figure 17.

Figures 18, 19 and 20 are views taken from the left side in figures 12, 13 and 14 respectively. The divider plate 19 can be seen in figures 19 and 20. The Flat flange extension 29 can be seen in Figure 20.

Figures 21 and 22 are perspective views corresponding respectively to figures 13 and 14. The plate 19 Divider can be seen in Figures 21 and 22. Extension 29 of flat flange can be seen in figure 22.

In the description above, the device split at the outlet 11 of the neck of the collector 7 takes the form of a flat plate. It should be noted that the dividing device may take other forms that achieve the required separation of Turbulent flows 13a, 13b in the opposite direction at exit 11 of neck. Figure 23 shows an example of a device 33 of alternative division, comprising a flat plate part 51 upper and a portion 53 of substantially cross section lower triangular that has concave sides. It should be noted that the cross section shown in figure 23 corresponds to the second part 39 in figure 9, and that the first part 37 in the Figure 9 stays the same, that is, a flat plate. Parts 51, 53 top and bottom of the dividing device 33 meet at a height corresponding to the height of the obtuse angle 55 in the figure 9.

Claims (5)

1. Gas turbine arrangement comprising: a conduit (1), of annular cross-section, for transporting combustion gases; located in the duct (1), turbine blades (3) to be driven by the flue gases; a diffuser (5), annularly, to diffuse the combustion gases following its conduit (1) through the turbine blades (3); and a manifold (7) for collecting the flue gases diffused by the diffuser (5), the manifold (7) comprising an annular main part (9), and, located in a position around the annular main part (9), a neck outlet (11), in which during the use of the gas turbine arrangement, the combustion gases collected by the manifold (7) are transported around the annular main part (9) of the manifold (7) in opposite directions until reaching the outlet (11) of the collector neck (7) moving in opposite directions, characterized in that the outlet of the neck (11) of the collector (7) includes a dividing device (19) whereby the flows in opposite direction at the neck outlet (11) is kept substantially separated, in which the turbine blades (3) revolve around a central line (A) of the gas turbine arrangement, and the dividing device (19) runs parallel to the center line (A), and extends radially te from the central line (A), in which the diffuser (5) has a mouth (35) whereby the flue gases leave the diffuser (5) and enter the manifold (7), the device (19) of division comprises a first part (37) that extends over the mouth (35) and a second part (39) that extends towards one side of the mouth (35), and the second part (39) extends radially inwards to a position (41) closer to the center line (A) than the mouth (35). 2. Arrangement according to claim 1, in the that the side of the first part (37) that is radially directed inward increases in distance from the center line (A) to as the distance increases from the second part (39). 3. Provision according to any one of the previous claims, wherein the device (19) of Division comprises a flat plate. 4. Provision according to any one of the previous claims, wherein the diffuser (5) has a curved protection flange (15) whereby the gases from combustion leave the diffuser (5) and enter the manifold (7), the protection flange (15) has an extension (29) that serves to increase the pressure recovery in the turbine arrangement of gas, and the extension (29) comprises a flat flange extension which is generally flat and forms a discontinuity with the curved protection flange (15). 5. Provision according to any one of the claims 1 to 3, wherein the diffuser (5) has a flange (15) curved protection by which flue gases leave the diffuser (5) and enter the manifold (7), the flange (15) of protection has an extension (31) that serves to increase pressure recovery in the gas turbine arrangement, and the extension (31) comprises a spiral flange extension that continue or extend the curvature of the protection flange (15) curved forming a spiral.