Patent Application
20160290642
The present disclosure relates to combustors for gas turbine engines and, in particular, to combustor configurations and components for gas turbine engines.
Gas turbine engines are required to operate efficiently during operation and flight. Theses engines create a tremendous amount of force and generate high levels of heat. As such, components of these engines are subjected to high levels of stress, temperature and pressure. It is necessary to provide components that can withstand the demands of a gas turbine engine. It is also desirable to provide components with increased operating longevity.
Conventional gas turbine engine combustors can include a combustor shell. The conventional combustor shell and its typical arrangement provide air flow to a combustor cavity. However, the conventional arrangements may result in regions experiencing distress due to the hot gas environment of the engine. Accordingly, there is a desire to improve combustion cooling and provide a configuration that allows for improved cooling characteristics. There is also a desire to improve the configuration of gas turbine engines and combustors.
Disclosed and claimed herein are combustor configurations and components for gas turbine engines. One embodiment is directed to a combustor for a gas turbine engine, the combustor including a support structure and a plurality of panels mounted to the structure, the plurality of panels defining a combustion cavity of the combustor. The plurality of panels include a first panel having a leading and trailing edge and a second panel having a leading edge and trailing edge, wherein a trailing edge of the first panel extends beyond the leading edge of the second panel and wherein the second panel is mounted to the support structure aft of the first panel.
In one embodiment, the support structure is an annular structure including an inner diameter structure and outer diameter structure, and wherein the plurality of panels are mounted to at least one of the inner diameter structure and outer diameter structure.
In one embodiment, the plurality of panels are heat shield panels.
In one embodiment, an air gap between the trailing edge of the first panel and the leading edge of the second panel forms at least a portion of a circumferential air gap for the combustor.
In one embodiment, the trailing edge of the first panel extends beyond the leading edge of the second panel to provide an air flow gap between the first and second panels and wherein portion of the first panel associated with the leading edge is configured to prevent a gas path flow within the combustor to enter the air flow gap.
In one embodiment, the first panel extends over the second panel along the entire length of the first panel by an amount within the range of 0.5 cm to 2 cm.
In one embodiment, the second panel includes effusion holes positioned along the leading edge of the second panel.
In one embodiment, the leading edge of the second panel is chamfered.
In one embodiment, the leading edge of the second panel includes one or more features to provide airflow when the trailing edge of the first panel contacts the leading edge of the second panel.
In one embodiment, the one or more features include groves in the leading edge of the second panel to provide said airflow.
Another embodiment is directed to a gas turbine engine including a combustor having a support structure and a plurality of panels mounted to the support structure. The plurality of panels define a combustion cavity of the combustor. The plurality of panels include a first panel having a leading and trailing edge, and a second panel having a leading edge and trailing edge, wherein a trailing edge of the first panel extends beyond the leading edge of the second panel and wherein the second panel is mounted to the support structure aft of the first panel.
In one embodiment, the support structure is an annular structure including an inner diameter structure and outer diameter structure, and wherein the plurality of panels are mounted to at least one of the inner diameter structure and outer diameter structure.
In one embodiment, the plurality of panels are heat shield panels.
In one embodiment, an air gap between the trailing edge of the first panel and the leading edge of the second panel forms at least a portion of a circumferential air gap for the combustor.
In one embodiment, the trailing edge of the first panel extends beyond the leading edge of the second panel to provide an air flow gap between the first and second panels and wherein portion of the first panel associated with the leading edge is configured to prevent a gas path flow within the combustor to enter the air flow gap.
In one embodiment, the first panel extends over the second panel along the entire length of the first panel by an amount within the range of 0.5 cm to 2 cm.
In one embodiment, the second panel includes effusion holes positioned along the leading edge of the second panel.
In one embodiment, leading edge of the second panel is chamfered.
In one embodiment, leading edge of the second panel includes one or more features to provide airflow when the trailing edge of the first panel contacts the leading edge of the second panel.
In one embodiment, the one or more features include groves in the leading edge of the second panel to provide said airflow.
Other aspects, features, and techniques will be apparent to one skilled in the relevant art in view of the following detailed description of the embodiments.
The features, objects, and advantages of the present disclosure will become more apparent from the detailed description set forth below when taken in conjunction with the drawings in which like reference characters identify correspondingly throughout and wherein:
One aspect of this disclosure relates to configurations for combustors according to one or more embodiments. In one embodiment, a configuration is provided for a combustor to prevent hot air/gas path egress to one or more air gaps of the combustor. According to one embodiment, panels may be configured with an extended portion to allow for the trailing edge of panels to extend over the leading edge of adjacent and downstream panels. In addition, one or more features may be provided to account for thermal growth of the panel interface.
As used herein, the terms “a” or “an” shall mean one or more than one. The term “plurality” shall mean two or more than two. The term “another” is defined as a second or more. The terms “including” and/or “having” are open ended (e.g., comprising). The term “or” as used herein is to be interpreted as inclusive or meaning any one or any combination. Therefore, “A, B or C” means “any of the following: A; B; C; A and B; A and C; B and C; A, B and C”. An exception to this definition will occur only when a combination of elements, functions, steps or acts are in some way inherently mutually exclusive.
Reference throughout this document to “one embodiment,” “certain embodiments,” “an embodiment,” or similar term means that a particular feature, structure, or characteristic described in connection with the embodiment is included in at least one embodiment. Thus, the appearances of such phrases in various places throughout this specification are not necessarily all referring to the same embodiment. Furthermore, the particular features, structures, or characteristics may be combined in any suitable manner on one or more embodiments without limitation.
According to one embodiment, combustor 105 may include one or more air gaps between panels 115. Air gaps between panels 115 may be associated with outer diameter structure 112 and/or inner diameter structure 113 of combustor 105. Exemplary regions for including air gaps are shown as 124 and 125 associated with outer diameter structure 112 and inner diameter structure 113, respectively. According to one embodiment, panels 115 associated with an air gap may include one or more features and configurations.
According to one embodiment, panels 115 may include a first panel 126 and a second panel 127 mounted to structure 110. First and second panels 126 and 127 have leading and trailing edges. Second panel 127 is mounted to the support structure aft of the first panel 126.
According to one embodiment, first panel 126 includes a trailing edge portion 135 which extends over leading edge 140 of second panel 127. The configuration of first panel 126 and a second panel 127 provides an air gap between the panels and allows for airflow 130 in the gap. Airflow 130 serves to both cool the extended lip of a trailing edge portion 135 of the first panel 126 (e.g., the upstream panel) and also lay a cooling film down on second panel 127 (e.g., the downstream panel). According to one embodiment, leading edge 140 of second panel 127 is chamfered.
According to one embodiment, first panel 126 is upstream (e.g., forward) from second panel 127. Similarly, second panel 127 is downstream (e.g., aft) of first panel 126. Although region 125 is shown and described as associated with inner diameter structure 113 it is equally appreciated that outer diameter 124 may include a similar configuration of a forward panel including a portion that overlaps an adjacent panel. It should also be appreciated that all panels along the circumferential gas path opening may include an overlapping configuration. As will be discussed in more detail below and according to another embodiment, an overlapping configuration may be employed to lateral portions (e.g., rails) of panel elements 115.
The position of leading edge 220 is identified as 225 such that the portion 230 that extends over the first panel 205 is identified as 230. According to one embodiment, second panel 210 includes chamfered region 235, which is angled down to allow for portion 230 to extend over chamfered region 235. An air gap between the trailing edge of the first panel 205 and the leading edge of the second panel 210 forms at least a portion of a circumferential air gap for the combustor. The trailing edge 215 of the first panel 205 extends beyond the leading edge 220 of the second panel 210 to provide an air flow gap between the first and second panels and wherein portion 230 of the first panel 205 associated with the leading edge is configured to prevent a gas path flow within the combustor to enter the air flow gap.
While this disclosure has been particularly shown and described with references to exemplary embodiments thereof, it will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the scope of the claimed embodiments.
This application is related to the concurrently filed application titled: COMBUSTOR PANELS AND CONFIGURATIONS FOR A GAS TURBINE ENGINE filed on Mar. 30, 2015 and assigned patent application Ser. No. ______, the disclosure of which is expressly incorporated by reference.
