Patent Grant
10267520
The subject matter disclosed herein generally relates to float wall combustor panels for gas turbine engines and, more particularly, air flow distribution features of float wall combustor panels and molds for making the same.
A combustor of a gas turbine engine may be configured and required to burn fuel in a minimum volume (e.g., a combustion chamber). Such configurations may place substantial heat load on the structure of the combustor. The heat loads may dictate that special consideration is given to structures which may be configured as heat shields or panels configured to protect the walls of the combustor, with the heat shields being air cooled.
The combustor of a gas turbine engine mixes and ignites compressed air with fuel, generating hot combustion gases. These hot combustion gases are then directed by the combustor to the turbine section of the engine where power is extracted from the hot gases. The walls of a combustor are lined with the heat shields or panels (e.g., float wall panels) that protect the body of the combustor liner from damage due to exposure with the hot gases.
Each float wall panel has several structural protrusions to offset the float wall panel from the combustor wall, providing a channel of airflow for cooling. The cooling pins also provide increased surface area for heat transfer from the float wall panel to the cooling airflow channel. During engine service operation, the combustor has to withstand extremely high temperatures, oxidizing, corrosive and erosive conditions. Thus, improved cooling flow arrangements for float wall panels may be desirable.
According to some embodiments, combustor panels for use in gas turbine engines are provided. The combustor panels include a panel body having a first side and a second side, a plurality of cooling pins extending from the first side, the plurality of cooling pins arranged in a pin array, wherein each cooling pin extends a first height from the first side of the panel body, has a pin diameter, and is separated from adjacent cooling pins of the pin array by a pin array separation distance, and at least one structural protrusion extending from the first side of the panel body. No pins of the pin array are located at a position within a flashing distance that is equal to a protrusion separation distance plus one half of the pin diameter, wherein the protrusion separation distance is a predetermined minimum distance between an exterior surface of the at least one structural protrusion and an exterior surface of a cooling pin, and wherein a location of the pin is measured from a center point of the cooling pin to a closest point on the exterior surface of the at least one structural protrusion. At least one pin array scallop is integrally formed with the at least one structural protrusion, the at least one pin array scallop forming a reduction in material on the at least one structural protrusion such that each cooling pin of the pin array that is closest to the at least one structural protrusion is positioned the pin array separation distance from the at least one structural protrusion.
In addition to one or more of the features described above, or as an alternative, further embodiments of the combustor panels may include that the at least one structural protrusion extends from the first side a distance greater than the first height;
In addition to one or more of the features described above, or as an alternative, further embodiments of the combustor panels may include that the at least one structural protrusion is at least one of a dilution hole boss and an attachment mechanism.
In addition to one or more of the features described above, or as an alternative, further embodiments of the combustor panels may include that the at least one structural protrusion includes a plurality of pin array scallops arranged around the at least one structural protrusion.
In addition to one or more of the features described above, or as an alternative, further embodiments of the combustor panels may include that the pin array separation distance is between 0.010 inches and 0.015 inches.
In addition to one or more of the features described above, or as an alternative, further embodiments of the combustor panels may include that the pin array separation distance is 0.013 inches.
According to some embodiments, combustors for gas turbine engines are provided. The combustors include a combustor shell and at least one combustor panel mounted to the combustor shell. The at least one combustor panel includes a panel body having a first side and a second side, a plurality of cooling pins extending from the first side, the plurality of cooling pins arranged in a pin array, wherein each cooling pin extends a first height from the first side of the panel body, has a pin diameter, and is separated from adjacent cooling pins of the pin array by a pin array separation distance, at least one structural protrusion extending from the first side of the panel body, wherein no pins of the pin array are located at a position within a flashing distance that is equal to a protrusion separation distance plus one half of the pin diameter, wherein the protrusion separation distance is a predetermined minimum distance between an exterior surface of the at least one structural protrusion and an exterior surface of a cooling pin, and wherein a location of the pin is measured from a center point of the cooling pin to a closest point on the exterior surface of the at least one structural protrusion, and at least one pin array scallop integrally formed with the at least one structural protrusion, the at least one pin array scallop forming a reduction in material on the at least one structural protrusion such that each cooling pin of the pin array that is closest to the at least one structural protrusion is positioned the pin array separation distance from the at least one structural protrusion.
In addition to one or more of the features described above, or as an alternative, further embodiments of the combustors may include that the at least one structural protrusion extends from the first side a distance greater than the first height;
In addition to one or more of the features described above, or as an alternative, further embodiments of the combustors may include that the at least one structural protrusion is a dilution hole boss arranged to allow dilution air to pass through the combustor shell and the combustor panel into a combustion chamber.
In addition to one or more of the features described above, or as an alternative, further embodiments of the combustors may include that the at least one structural protrusion is an attachment mechanism, wherein the attachment mechanism fixedly attaches the at least one combustor panel to the combustor shell.
In addition to one or more of the features described above, or as an alternative, further embodiments of the combustors may include that the at least one structural protrusion includes a plurality of pin array scallops arranged around the at least one structural protrusion.
In addition to one or more of the features described above, or as an alternative, further embodiments of the combustors may include that the pin array separation distance is between 0.010 inches and 0.015 inches.
In addition to one or more of the features described above, or as an alternative, further embodiments of the combustors may include that the pin array separation distance is 0.013 inches.
In addition to one or more of the features described above, or as an alternative, further embodiments of the combustors may include that the at least one combustor panel is positioned with the second side exposed to a combustion chamber and a cooling flow passes between the combustor shell and the at least one combustor panel along the first side, wherein the pin array provides thermal transfer between the at least one combustor panel and the cooling flow.
In addition to one or more of the features described above, or as an alternative, further embodiments of the combustors may include that the at least one pin array scallop alters the cooling flow around the at least one structural protrusion to prevent hot zones on the at least one combustor panel at locations downstream of the at least one structural protrusion in a direction of flow of the cooling flow.
In addition to one or more of the features described above, or as an alternative, further embodiments of the combustors may include that the at least one combustor panel is a float wall combustor panel.
The foregoing features and elements may be combined in various combinations without exclusivity, unless expressly indicated otherwise. These features and elements as well as the operation thereof will become more apparent in light of the following description and the accompanying drawings. It should be understood, however, the following description and drawings are intended to be illustrative and explanatory in nature and non-limiting.
The subject matter is particularly pointed out and distinctly claimed at the conclusion of the specification. The foregoing and other features, and advantages of the present disclosure are apparent from the following detailed description taken in conjunction with the accompanying drawings in which:
The gas turbine engine 20 generally includes a low speed spool 30 and a high speed spool 32 mounted for rotation about an engine centerline longitudinal axis A. The low speed spool 30 and the high speed spool 32 may be mounted relative to an engine static structure 33 via several bearing systems 31. It should be understood that other bearing systems 31 may alternatively or additionally be provided.
The low speed spool 30 generally includes an inner shaft 34 that interconnects a fan 36, a low pressure compressor 38 and a low pressure turbine 39. The inner shaft 34 can be connected to the fan 36 through a geared architecture 45 to drive the fan 36 at a lower speed than the low speed spool 30. The high speed spool 32 includes an outer shaft 35 that interconnects a high pressure compressor 37 and a high pressure turbine 40. In this embodiment, the inner shaft 34 and the outer shaft 35 are supported at various axial locations by bearing systems 31 positioned within the engine static structure 33.
A combustor 102 is arranged between the high pressure compressor 37 and the high pressure turbine 40. A mid-turbine frame 44 may be arranged generally between the high pressure turbine 40 and the low pressure turbine 39. The mid-turbine frame 44 can support one or more bearing systems 31 of the turbine section 28. The mid-turbine frame 44 may include one or more airfoils 46 that extend within the core flow path C.
The inner shaft 34 and the outer shaft 35 are concentric and rotate via the bearing systems 31 about the engine centerline longitudinal axis A, which is co-linear with their longitudinal axes. The core airflow is compressed by the low pressure compressor 38 and the high pressure compressor 37, is mixed with fuel and burned in the combustor 102, and is then expanded over the high pressure turbine 40 and the low pressure turbine 39. The high pressure turbine 40 and the low pressure turbine 39 rotationally drive the respective high speed spool 32 and the low speed spool 30 in response to the expansion.
The pressure ratio of the low pressure turbine 39 can be the pressure measured prior to the inlet of the low pressure turbine 39 as related to the pressure at the outlet of the low pressure turbine 39 and prior to an exhaust nozzle of the gas turbine engine 20. In one non-limiting embodiment, the bypass ratio of the gas turbine engine 20 is greater than about ten (10:1), the fan diameter is significantly larger than that of the low pressure compressor 38, and the low pressure turbine 39 has a pressure ratio that is greater than about five (5:1). It should be understood, however, that the above parameters are only examples of one embodiment of a geared architecture engine and that the present disclosure is applicable to other gas turbine engines, including direct drive turbofans.
In this embodiment of the example gas turbine engine 20, a significant amount of thrust is provided by the bypass flow path B due to the high bypass ratio. The fan section 22 of the gas turbine engine 20 is designed for a particular flight condition—typically cruise at about 0.8 Mach and about 35,000 feet. This flight condition, with the gas turbine engine 20 at its best fuel consumption, is also known as bucket cruise Thrust Specific Fuel Consumption (TSFC). TSFC is an industry standard parameter of fuel consumption per unit of thrust.
Fan Pressure Ratio is the pressure ratio across a blade of the fan section 22 without the use of a Fan Exit Guide Vane system. The low Fan Pressure Ratio according to one non-limiting embodiment of the example gas turbine engine 20 is less than 1.45. Low Corrected Fan Tip Speed is the actual fan tip speed divided by an industry standard temperature correction of [(Tram ° R)/(518.7° R)]0.5, where T represents the ambient temperature in degrees Rankine. The Low Corrected Fan Tip Speed according to one non-limiting embodiment of the example gas turbine engine 20 is less than about 1150 fps (351 m/s).
Each of the compressor section 24 and the turbine section 28 may include alternating rows of rotor assemblies and vane assemblies (shown schematically) that carry airfoils that extend into the core flow path C. For example, the rotor assemblies can carry a plurality of rotating blades 25, while each vane assembly can carry a plurality of vanes 27 that extend into the core flow path C. The blades 25 of the rotor assemblies create or extract energy (in the form of pressure) from the core airflow that is communicated through the gas turbine engine 20 along the core flow path C. The vanes 27 of the vane assemblies direct the core airflow to the blades 25 to either add or extract energy.
In the configuration shown in
The combustor 102, as will be appreciated by those of skill in the art, includes one or more combustor panels 126, 128 that are mounted on an interior surface of one or more combustor shells 130 and are configured parallel to the combustor shell 130 (whether at the inner or outer diameter). The combustor panels 126, 128 can be removably mounted to the combustor shell 130 by one or more attachment mechanisms 132. In some embodiments, the attachment mechanisms 132 can be integrally formed with a respective combustor panel 126, 128 and/or the combustor shell 130, although other configurations are possible. In some embodiments, the attachment mechanisms 132 are bolts or other structures that extend from the respective combustor panel 126, 128 through the interior surface thereof to a receiving portion or aperture of the combustor shell 130 such that the panel 126, 128 can be attached to the combustor shell 130 and held in place.
The combustor panels 126, 128 may include a plurality of cooling holes and/or apertures (e.g., dilution holes) to enable fluid, such as gases, to flow from areas external to the combustion chamber 104 into the combustion chamber 104. Cooling may be provided from the shell-side of the panels 126, 128 and hot gases may be in contact with the combustion-side of the panels 126, 128 during combustion within the combustion chamber 104. That is, hot gases may be in contact with a surface of the panels 126, 128 that is facing the combustion chamber 104. The combustor panels 126, 128 may be float wall panels, as will be appreciated by those of skill in the art.
First panels 126, as shown in
Combustor panels, such as shown in
Turning now to
The cold side 138 of the panel body 136 includes a plurality of cooling pins 140 extending outwardly therefrom (e.g., toward shroud chamber 113 when installed within the combustion section 26). In one non-limiting example, the panel body 136 of the combustor panel 126 can be made of cast nickel based super-alloys while the cooling pins 140 can be made of cast or wrought nickel based alloys. In other embodiments, the panel body 136 and the cooling pins 140 are formed in a single casting and formed from the same material. In a non-limiting example, the cooling pins 140 may be formed with a diameter between 0.020 inches and 0.060 inches and have a length of extension from the cold side 138 between 0.020 inches and 0.200 inches.
The panel body 136 also includes a plurality of attachment mechanism 132 that extend outwardly from the cold side 138 of the panel body 136 for attachment of the combustor panel 126 to the combustor shell 130, as shown in
Also extending from the cold side 138 of the panel body 136 are the dilution hole bosses 144 and the attachment mechanisms 132 (referred to herein generically as “structural protrusions,” which may encompass other structures extending from the cold side of a combustor panel). As shown in
During a casting process used to manufacture the combustor panel 126, producibility issues may arise with respect to the formation of the cooling pins 140 that are close to or in near proximity to features that extend from the cold side 138 (e.g., attachment mechanisms 132, dilution hole bosses 144, etc.). For example, as shown in
Turning to
Turning to
Turning now to
In a manufacturing process of the combustor panel, flashing may occur when a cooling pin 440 is within a flashing distance μ. The flashing distance μ is a distance between a center point 452 of a cooling pin 440 and the closest point on a boss exterior surface 454 of the structural protrusion 444. Stated another way a protrusion separation distance γ is defined as the minimum distance between the boss exterior surface 454 and a pin exterior surface 456. As such, the flashing distance μ is equal to the protrusion separation distance γ plus one half of the pin diameter β (i.e., μ=γ+β/2). In some non-limiting embodiments, the pin array separation distance α and the protrusion separation distance γ may be equal. As an illustrative example, in some arrangements, the pin array may be defined with a pin array separation distance α of approximately 10-15 mil (0.010 to 0.015 inches), and in some specific embodiments, the pin array separation distance α may be about 13 mil (0.013 inches). The pin array separation distance α may be a tolerance (e.g., minimum distance) based on a casting or other manufacturing limitation. As will be appreciated by those of skill in the art, the protrusion separation distance γ is similar to the minimum separation distance D0 shown in
In accordance with embodiments of the present disclosure, combustor panels are modified to address the drawbacks of having flashing (with cooling pins within the minimum separation distance D0) and/or associated with voids formed by the elimination of such cooling pins (e.g., voids 346 shown in
In order to optimize both castability and airflow cooling through the pin array, the boss (or other extending features) can be scalloped in an intermittent fashion to form pin array scallops to enable the pin array configuration to exist in problematic casting zones. The pin array scallops, in accordance with embodiments of the present disclosure, can be located around the structural protrusion where a cooling pin following the pin array pattern would occur within the minimum separation distance. Such pin array scallops can prevent leakage into the circumferential area around the boss (e.g., voids 346 shown in
Turning now to
As shown in
the a pin array scallop 558 is formed on the structural protrusion 544 and the cooling pin 540 is maintained as part of the pin array. The pin array scallops 558 are shaped and sized such that no portion of the structural protrusion 544 is closer to an adjacent cooling pin 540 than the pin array separation distance (e.g., pin array separation distance α shown in
As shown in
The combustor panel 526, in some embodiments, is formed from a mold with liquid metal poured into the mold. Typically, this molding process can cause the flashing described above. However, because the molds can be formed to have the shape/geometry with the pin array scallops around the molds for the structural protrusions, no flashing may occur and improved casting processes can be achieved. Accordingly, some embodiments of the present disclosure are directed to molds for forming combustor panels as described herein. As will be appreciated by those of skill in the art, the molds are “negatives” of the combustor panels illustrated herein. Thus, for example referring to
The use of the terms “a,” “an,” “the,” and similar references in the context of description (especially in the context of the following claims) are to be construed to cover both the singular and the plural, unless otherwise indicated herein or specifically contradicted by context. The modifier “about” and/or “approximately” used in connection with a quantity is inclusive of the stated value and has the meaning dictated by the context (e.g., it includes the degree of error associated with measurement of the particular quantity). All ranges disclosed herein are inclusive of the endpoints, and the endpoints are independently combinable with each other. It should be appreciated that relative positional terms such as “forward,” “aft,” “upper,” “lower,” “above,” “below,” “radial,” “axial,” “circumferential,” and the like are with reference to normal operational attitude and should not be considered otherwise limiting.
While the present disclosure has been described in detail in connection with only a limited number of embodiments, it should be readily understood that the present disclosure is not limited to such disclosed embodiments. Rather, the present disclosure can be modified to incorporate any number of variations, alterations, substitutions, combinations, sub-combinations, or equivalent arrangements not heretofore described, but which are commensurate with the spirit and scope of the present disclosure. Additionally, while various embodiments of the present disclosure have been described, it is to be understood that aspects of the present disclosure may include only some of the described embodiments.
Accordingly, the present disclosure is not to be seen as limited by the foregoing description, but is only limited by the scope of the appended claims.
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| Number | Date | Country | |
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| 20190049115 A1 | Feb 2019 | US |
