Turbomachine combustor assembly including a vortex modification system

BACKGROUND OF THE INVENTION

p-0002The subject matter disclosed herein relates to the art of turbomachines and, more particularly, to a turbomachine combustor including a vortex modification system.

p-0003In general, gas turbine engines combust a fuel/air mixture that releases heat energy to form a high temperature gas stream. The high temperature gas stream is channeled to a turbine via a hot gas path. The turbine converts thermal energy from the high temperature gas stream to mechanical energy that rotates a turbine shaft. The turbine may be used in a variety of applications, such as for providing power to a pump or an electrical generator.

p-0004Many gas turbines include an annular combustor within which are formed the combustion gases that create the high temperature gas stream. Other turbomachines employ a plurality of combustors arranged in a can-annular array. In such a turbomachine, the combustion gases are formed in each of the plurality of combustors, combusted in a combustion chamber defined by a combustor body, and delivered to the turbine through a transition piece. Often times, compressor discharge air is passed into the combustor to cool various surfaces and aid in forming the fuel/air mixture. In certain arrangements, compressor discharge air is often channeled along a combustor liner toward a venturi.

p-0005A portion of the compressor discharge air is directed onto internal surfaces of the venturi for cooling. The compressor discharge air passes from the venturi into a passage formed between the combustor body and the combustor liner. In certain arrangements, a plurality of turbulator members is arranged in the passage. The turbulator members create flow vortices that enhance heat transfer in the combustor body. The compressor discharge air exits the passage into the combustion chamber to mix with the combustion gases.

BRIEF DESCRIPTION OF THE INVENTION

p-0006According to one aspect of the exemplary embodiment, a turbomachine combustor assembly includes a combustor body, and a combustor liner arranged within the combustor body and defining a combustion chamber. The combustor liner includes a venturi portion arranged within the combustion chamber. A fluid passage is defined between the combustor body and the combustor liner, and at least one turbulator is arranged in the fluid passage. The at least one turbulator is configured and disposed to create vortices in the fluid passage. A vortex modification system is arranged at the fluid passage and is configured and disposed to disrupt the vortices.

p-0007According to another aspect of the exemplary embodiment a turbomachine includes a compressor portion, a turbine portion, and a combustor assembly fluidly connecting the compressor portion and the turbine portion. The combustor assembly includes a combustor body, and a combustor liner arranged within the combustor body and defining a combustion chamber. The combustor liner includes a venturi portion arranged within the combustion chamber. A fluid passage is defined between the combustor body and the combustor liner, and at least one turbulator is arranged in the fluid passage. The at least one turbulator is configured and disposed to create vortices in the fluid passage. A vortex modification system is arranged at the fluid passage and is configured and disposed to disrupt the vortices.

p-0008According to yet another aspect of the exemplary embodiment, a method of mitigating undesirable noise in a combustor assembly with compressor discharge air includes passing compressor discharge air into a venturi portion arranged within the combustor assembly, guiding the compressor discharge air across interior surfaces of the venturi portion to provide cooling, passing the compressor discharge air from the venturi portion into a fluid passage defined in the combustor assembly, creating vortices in the compressor discharge air passing through the fluid passage to facilitate heat exchange, and disrupting the vortices in the compressor discharge air to minimize undesirable noise in the combustor assembly.

p-0009These and other advantages and features will become more apparent from the following description taken in conjunction with the drawings.

BRIEF DESCRIPTION OF THE DRAWINGS

p-0010The subject matter, which is regarded as the invention, is particularly pointed out and distinctly claimed in the claims at the conclusion of the specification. The foregoing and other features, and advantages of the invention are apparent from the following detailed description taken in conjunction with the accompanying drawings in which:

p-0011<figref idrefs="DRAWINGS">FIG. 1</figref> is a schematic view of a turbomachine including a combustor assembly having a vortex modification system in accordance with an exemplary embodiment;

p-0012<figref idrefs="DRAWINGS">FIG. 2</figref> is a partial cross-sectional side view of the combustor assembly of <figref idrefs="DRAWINGS">FIG. 1</figref> illustrating a vortex modification system in accordance with one aspect of the exemplary embodiment;

p-0013<figref idrefs="DRAWINGS">FIG. 3</figref> is a detail view of the vortex modification system of <figref idrefs="DRAWINGS">FIG. 2</figref> showing a jet member positioned adjacent a downstream end turbulator;

p-0014<figref idrefs="DRAWINGS">FIG. 4</figref> is a detail view of a vortex modification system in accordance with another aspect of the exemplary embodiment illustrating a jet member positioned between adjacent ones of a plurality of turbulators;

p-0015<figref idrefs="DRAWINGS">FIG. 5</figref> depicts jet members in accordance with one aspect of the exemplary embodiment;

p-0016<figref idrefs="DRAWINGS">FIG. 6</figref> depicts jet members in accordance with another aspect of the exemplary embodiment;

p-0017<figref idrefs="DRAWINGS">FIG. 7</figref> depicts jet members in accordance with yet another aspect of the exemplary embodiment;

p-0018<figref idrefs="DRAWINGS">FIG. 8</figref> illustrates a vortex modification system in accordance with another aspect of the exemplary embodiment;

p-0019<figref idrefs="DRAWINGS">FIG. 9</figref> illustrates a vortex modification system in accordance with still another aspect of the exemplary embodiment;

p-0020<figref idrefs="DRAWINGS">FIG. 10</figref> illustrates a vortex modification system in accordance with yet another aspect of the exemplary embodiment; and

p-0021<figref idrefs="DRAWINGS">FIG. 11</figref> illustrates a vortex modification system in accordance with still yet another aspect of the exemplary embodiment.

p-0022The detailed description explains embodiments of the invention, together with advantages and features, by way of example with reference to the drawings.

DETAILED DESCRIPTION OF THE INVENTION

p-0023With reference to <figref idrefs="DRAWINGS">FIG. 1</figref>, a turbomachine constructed in accordance with an exemplary embodiment is indicated generally at <b>2</b>. Turbomachine <b>2</b> includes a compressor portion <b>4</b> and a turbine portion <b>6</b>. Compressor portion <b>4</b> includes a compressor housing <b>8</b> and turbine portion <b>6</b> includes a turbine housing <b>10</b>. Compressor portion <b>4</b> is linked to turbine portion <b>6</b> through a common compressor/turbine shaft or rotor <b>16</b>. Compressor portion <b>4</b> is also linked to turbine portion <b>6</b> through a plurality of circumferentially spaced combustor assemblies, one of which is indicated at <b>20</b>.

p-0024As best shown in <figref idrefs="DRAWINGS">FIG. 2</figref>, combustor assembly <b>20</b> includes a combustor body <b>34</b> having a forward end <b>36</b> to which is mounted an injector nozzle housing <b>37</b>. Combustor body <b>34</b> includes an outer surface <b>38</b> and an inner surface <b>39</b>. In the exemplary embodiment shown, combustor assembly <b>20</b> includes a combustor liner <b>43</b> arranged within combustor body <b>34</b>. Combustor liner <b>43</b> includes an inner surface <b>44</b> and an outer surface <b>45</b>. Outer surface <b>45</b> is spaced from an inner surface <b>39</b> forming a passage <b>46</b> that transmits compressor discharge air from compressor portion <b>4</b> toward injector nozzle housing <b>37</b>. Inner surface <b>44</b> of combustor liner <b>43</b> defines a combustion chamber <b>48</b>. In further accordance with the exemplary embodiment shown, combustor assembly <b>20</b> includes a venturi portion <b>50</b> provided on combustor liner <b>43</b> in combustion chamber <b>48</b>. Venturi portion <b>50</b> defines a venturi throat <b>52</b> that operates to stabilize a combustible mixture passing through combustion chamber <b>48</b>.

p-0025In the exemplary embodiment shown in <figref idrefs="DRAWINGS">FIGS. 2 and 3</figref>, venturi portion <b>50</b> includes an outer surface <b>56</b> that is exposed to combustion gases in combustion chamber <b>48</b> and an inner surface <b>57</b> that defines an inner venturi section <b>59</b>. Venturi portion <b>50</b> is also shown to include an inner venturi plate <b>62</b> arranged within inner venturi section <b>59</b> and a venturi wall <b>64</b> that extends downstream in combustion chamber <b>48</b>. Venturi wall <b>64</b> includes an outer surface <b>67</b> and an inner surface <b>68</b>. Inner surface <b>68</b> of venturi wall <b>64</b> is spaced from inner surface <b>44</b> of combustor liner <b>43</b> forming a fluid passage <b>74</b>. With this arrangement, inner venturi plate <b>62</b> directs a portion of the compressor discharge air passing through passage <b>46</b> onto inner surface <b>57</b> of venturi portion <b>50</b>. The portion of compressor discharge air passes over inner surface <b>57</b> to provide cooling at venturi portion <b>50</b> before passing into fluid passage <b>74</b> and discharging into combustion chamber <b>48</b>.

p-0026As further shown in the exemplary embodiment, a plurality of turbulators <b>80</b> is arranged on venturi wall <b>64</b>. Turbulators <b>80</b> extend between an upstream end turbulator <b>81</b> and a downstream end turbulator <b>82</b>. Turbulators <b>80</b> create vortices in the portion of compressor discharge air passing through fluid passage <b>74</b>. The vortices enhance heat transfer between venturi wall <b>64</b> and combustor liner <b>43</b>. However, the vortices have been shown to create undesirable high frequency noise in combustor assembly <b>20</b>. In order to mitigate the undesirable noise, combustor assembly <b>20</b> includes a vortex modification system <b>86</b>. In accordance with the exemplary aspect shown, vortex modification system <b>86</b> includes a jet member <b>90</b> formed in combustor liner <b>43</b> and positioned downstream from downstream end turbulator <b>82</b>. Jet member <b>90</b> directs a stream of fluid at the portion of combustor discharge air passing through fluid passage <b>74</b>. The fluid passing from jet member <b>90</b> disrupts the vortices imparted to the portion of combustor discharge air created by turbulators <b>80</b> to mitigate undesirable noise in combustor assembly <b>20</b>.

p-0027Reference will now be made to <figref idrefs="DRAWINGS">FIG. 4</figref>, wherein like reference numbers represent corresponding parts in the respective views, in describing a vortex modification system <b>104</b> in accordance with another aspect of the exemplary embodiment. Vortex modification system <b>104</b> includes a plurality of jet members <b>106</b>-<b>111</b> formed in combustor liner <b>43</b>. As best shown in <figref idrefs="DRAWINGS">FIG. 5</figref>, jet members <b>106</b>-<b>111</b> have a circular cross-section. Jet members <b>106</b>-<b>111</b> are positioned between adjacent ones of turbulators <b>80</b>. With this arrangement, jet members <b>106</b>-<b>111</b> disrupt the vortices created at each turbulator <b>80</b>. The disruption of the vortices does not interfere with heat transfer properties but does mitigate undesirable noise in combustor assembly <b>20</b>. Actually, it has been found that the disruption of the vortices may enhance heat transfer characteristics of the portion of compressor discharge air passing through fluid passage <b>74</b>. At this point it should be understood that jet members can take on a variety of forms. For example, <figref idrefs="DRAWINGS">FIG. 6</figref> illustrates jet members <b>114</b> and <b>115</b> having non-circular or an oval shaped cross section. <figref idrefs="DRAWINGS">FIG. 7</figref> illustrates jet members <b>118</b> and <b>119</b> having non-circular or rectangular cross-section. The particular shape of jet members <b>106</b>-<b>111</b> is not limited to those examples shown. It should be understood that jet member <b>90</b> could also take on a variety of forms.

p-0028Reference will now be made to <figref idrefs="DRAWINGS">FIG. 8</figref>, wherein like reference numbers represent corresponding parts in the respective views, in describing a vortex modification system <b>130</b> in accordance with yet another aspect of the exemplary embodiment. Vortex modification system <b>130</b> takes the form of vortex modifying turbulators <b>133</b>-<b>138</b>. Vortex modifying turbulators <b>133</b>-<b>138</b> include a rounded end portion, such as shown at <b>140</b> on vortex modifying turbulator <b>133</b>, that disrupts vortices created in fluid passage <b>74</b>. The shape and number of vortex modifying turbulators can vary. For example, in accordance with the exemplary aspect shown, fluid passage <b>74</b> may include as few as one vortex modifying turbulator or all turbulators may be modified to create vortices that do not promote the creation of undesirable noise in combustor assembly <b>20</b> while also ensuring a desired heat transfer from venturi wall <b>64</b> to combustor liner <b>43</b>.

p-0029Reference will now be made to <figref idrefs="DRAWINGS">FIG. 9</figref>, wherein like reference numbers represent corresponding parts in the respective views, in describing a vortex modification system <b>142</b> in accordance with still another aspect of the exemplary embodiment. Vortex modification system <b>142</b> includes a plurality of turbulators <b>144</b>-<b>148</b> arranged on inner surface <b>68</b> of venturi wall <b>64</b>. In the exemplary embodiment shown, vortex modification is achieved by varying a spacing between adjacent ones of turbulators <b>144</b>-<b>148</b>. For example, spacing between turbulators <b>144</b> and <b>145</b> is different from a spacing between turbulators <b>145</b> and <b>146</b>. The variation in spacing disrupts vortices created in fluid passage <b>74</b> to mitigate the creation of undesirable noise in combustor assembly <b>20</b> while also ensuring a desired heat transfer from venturi wall <b>64</b> to combustor liner <b>43</b>.

p-0030Reference will now be made to <figref idrefs="DRAWINGS">FIG. 10</figref>, wherein like reference numbers represent corresponding parts in the respective views, in describing a vortex modification system <b>153</b> in accordance with still another aspect of the exemplary embodiment. Vortex modification system <b>153</b> includes a first plurality of turbulators <b>155</b>-<b>162</b>, and a second plurality of turbulators <b>165</b>-<b>167</b> mounted to inner surface <b>68</b> of venturi wall <b>64</b>. The first plurality of turbulators <b>155</b>-<b>162</b> is configured to create a first plurality of vortices in fluid passage <b>74</b>. The second plurality of turbulators <b>165</b>-<b>167</b> have a height relative to inner surface <b>68</b> that is distinct from a height of first plurality of turbulators <b>155</b>-<b>162</b>. In the exemplary embodiment shown, second plurality of turbulators <b>165</b>-<b>167</b> have a height relative to inner surface <b>68</b> that is greater than the height of first plurality of turbulators <b>155</b>-<b>162</b>. In this manner, first plurality of turbulators <b>155</b>-<b>162</b> constitute vortex modifying turbulators that are configured to create a second plurality of vortices in fluid passage <b>74</b>. The second plurality of vortices are configured to disrupt the first plurality of vortices in order to mitigate the creation of undesirable noise in combustor <b>20</b> while also ensuring a desired heat transfer from venturi wall <b>64</b> to combustor liner <b>43</b>.

p-0031Reference will now be made to <figref idrefs="DRAWINGS">FIG. 11</figref>, wherein like reference numbers represent corresponding parts in the respective views, in describing a vortex modification system <b>180</b> in accordance with still another aspect of the exemplary embodiment. Vortex modification system <b>180</b> includes a first plurality of turbulators <b>183</b>-<b>188</b> and a second plurality of turbulators <b>194</b>-<b>195</b> mounted to inner surface <b>68</b> of venturi wall <b>64</b>. The first plurality of turbulators <b>183</b>-<b>188</b> are configured to create a first plurality of vortices in fluid passage <b>74</b>. The second plurality of turbulators <b>194</b>-<b>195</b> have a height relative to inner surface <b>68</b> that is distinct from a height of first plurality of turbulators <b>183</b>-<b>188</b> and thus constitute vortex modifying turbulators. In the exemplary embodiment shown, second plurality of turbulators <b>194</b>-<b>195</b> have a height relative to inner surface <b>68</b> that is greater than the height of first plurality of turbulators <b>183</b>-<b>188</b>. In this manner, first plurality of turbulators <b>183</b>-<b>188</b> constitute vortex modifying turbulators that are configured to create a second plurality of vortices in fluid passage <b>74</b>.

p-0032In addition, a spacing between the first plurality of turbulators <b>183</b>-<b>188</b> and the second plurality of turbulators <b>194</b>-<b>195</b> is varied to further disrupt vortices in fluid passage <b>74</b>. Of course it should be understood that spacing between adjacent ones of the first plurality of turbulators <b>183</b>-<b>188</b> and/or between adjacent ones of the second plurality of turbulators could also vary. The second plurality of turbulators along with the varied spacing between turbulators collectively operate to disrupt the first plurality of vortices in order to mitigate the creation of undesirable noise in combustor <b>20</b> while also ensuring a desired heat transfer from venturi wall <b>64</b> to combustor liner <b>43</b>.

p-0033At this point it should be understood that the exemplary embodiment provides a system that not only generates vortices in a combustor fluid passage to enhance heat transfer, but also a system for disrupting those vortices to mitigate noise in the combustor. It should also be understood that the number of turbulators could vary. It should be further recognized that the number, size and shape of vortex modifying turbulators could also vary.

p-0034While the invention has been described in detail in connection with only a limited number of embodiments, it should be readily understood that the invention is not limited to such disclosed embodiments. Rather, the invention can be modified to incorporate any number of variations, alterations, substitutions or equivalent arrangements not heretofore described, but which are commensurate with the spirit and scope of the invention. Additionally, while various embodiments of the invention have been described, it is to be understood that aspects of the invention may include only some of the described embodiments. Accordingly, the invention is not to be seen as limited by the foregoing description, but is only limited by the scope of the appended claims.