Stator air chamber with collet seal

Abstract

Methods, apparatus, systems, and articles of manufacture are disclosed to implement a stator plenum with collet seal. A stator plenum for a gas turbine engine includes an outer shell surrounding a centerline axis; a first end of the outer shell coupled to an engine casing at a first coupling, the first coupling forming a first seal; a second end of the outer shell coupled to the engine casing at a second coupling, the second end formed by a thickened portion of the outer shell, the second coupling forming a second seal; and a cavity formed by the outer shell, the cavity containing a cooling flow to reduce a temperature of the turbine.

Description

[0001] Statement as to Federally Sponsored Research or Development

[0002] This invention was made with U.S. Government support under. The U.S. Government can have certain rights in the invention. TECHNICAL FIELD

[0003] The present disclosure relates generally to stators for gas turbines, and more particularly, to stator plenums with collet seals. BACKGROUND

[0004] Gas turbine engines generally include, in serial flow order, an inlet section, a compressor section, a combustion section, a turbine section, and an exhaust section. In operation, air enters the inlet section and flows to the compressor section where one or more axial compressors progressively compress the air until it reaches the combustion section, producing combustion gases. The combustion gases flow from the combustion section through a hot gas path defined within the turbine section, and then exit the turbine section via the exhaust section. BRIEF DESCRIPTION OF DRAWINGS

[0005] Figure 1 An example gas turbine engine is shown.

[0006] Figure 2 An example cross-sectional side view of a core turbine of an example gas turbine engine is shown.

[0007] Figure 3 An example cross-sectional side view of a first example stator plenum is shown.

[0008] Figure 4 An example cross-sectional side view of a second example stator plenum is shown.

[0009] Figure 5 An example cross-sectional side view of a third example stator plenum is shown.

[0010] Figure 6 An example cross-sectional side view of a fourth example stator plenum is shown.

[0011] Figure 7 An example cross-sectional side view of a fifth example stator plenum is shown.

[0012] The drawings are not drawn to scale. Rather, the thickness of layers or regions can be exaggerated in the drawings for clarity. Although layers and regions are shown to have clear lines and boundaries, some or all of these lines and / or boundaries can be idealized. In reality, the boundaries and / or lines can be obscured, blended, and / or irregular. Generally, the same reference numbers are used throughout the drawings and accompanying written description to refer to the same or like parts. As used herein, unless otherwise stated, the term“over” describes a relationship between two parts relative to the Earth. A first part is over a second part if the second part is between the Earth and the first part. Likewise, as used herein, a first part is“under” a second part when the first part is closer to the Earth than the second part. As noted above, a first part can be over or under a second part with one or more of: having other parts in between, having no other parts in between, the first and second parts being in contact, or the first and second parts not being in direct contact with each other. As used in this patent, a statement that any part (e.g., layer, film, zone, region, or plate) is on (e.g., positioned on, located on, disposed on, or formed on, etc.) another part means that the part is in contact with the other part, or that the part is located above the other part with one or more intervening parts in between. As used herein, unless otherwise stated, a connection reference (e.g., attached, coupled, connected, and joined) can include intervening members between the elements to which the connection reference refers and / or relative movement between those elements. Thus, a connection reference does not necessarily infer that two elements are directly connected and / or have a fixed relationship with one another. As used herein, a statement that any part is“in contact” with another part is defined to mean that there are no intervening parts between the two parts.

[0013] Unless specifically stated otherwise, as used herein, descriptors such as "first," "second," "third," etc. do not connote or otherwise imply any priority, physical order, arrangement in a list, and / or any ordering whatsoever, but are merely used as labels and / or arbitrary names to identify elements so that the disclosed examples can be understood. In some examples, a descriptor "first" can be used to refer to an element in the detailed description, while a different descriptor (e.g., "second" or "third") can be used in the claims to refer to the same element. In such instances, it should be understood that such descriptors are used merely to clearly identify those elements that can otherwise share the same name, for example. As used herein, "approximately" and "about" mean dimensions that can not be exact due to manufacturing tolerances and / or other real-world imperfections. As used herein, "substantially the same dimensions" means dimensions that can not be exactly the same due to manufacturing tolerances and / or other real-world imperfections. Thus, "substantially the same dimensions" means + / - 10% of the dimensions, unless otherwise specified. As used herein, the phrase "in communication," including variations thereof, encompasses both direct and / or indirect communication through one or more intermediary components and does not require direct physical (e.g., wired) communication and / or continuous communication, but additionally includes selective communication at periodic intervals, predetermined intervals, non-periodic intervals, and / or one-time events. DETAILED DESCRIPTION

[0014] During normal engine operation, one or more portions of the engine generate heat. Heat (e.g., thermal energy) can cause engine performance to decrease and components to wear. There is a continuing need to reduce the heat generated during engine operation. Certain examples provide a stator plenum with collet seals that can reduce heat (e.g., provide cooling) on engine components (e.g., high pressure turbine, low pressure turbine, etc.), thereby improving engine performance and durability. Examples disclosed herein utilize compressor discharge air to reduce heat in downstream engine components and, thus, improve engine efficiency.

[0015] In the following detailed description, reference is made to the accompanying drawings that form a part hereof, and in which are shown, by way of illustration, specific examples in which embodiments can be practiced. These examples are described in sufficient detail to enable those skilled in the art to practice the subject matter, and it is to be understood that other examples can be utilized. The following detailed description is, therefore, not to be taken in a limiting sense, as the scope of the subject matter described herein is broadly contemplated. Certain features from the various aspects of the following description can be combined to form yet further aspects of the subject matter discussed below.

[0016] The descriptors“first,”“second,”“third,” etc. are used herein to identify multiple elements or components that can be individually referred to. Unless otherwise specified or understood from its usage context, such descriptors are not intended to impart priority, physical order or arrangement in a list, or any meaning in time ordering, but are merely used as labels to individually refer to multiple elements or components for ease of understanding the disclosed examples. In some examples, the descriptor“first” can be used to refer to an element in the detailed description, while a different descriptor (e.g.,“second” or“third”) can be used in the claims to refer to the same element. In such instances, it is understood that such descriptors are used merely for ease of referring to multiple elements or components.

[0017] The terms“upstream” and“downstream” refer to relative directions with respect to fluid flow in a fluid path. For example,“upstream” refers to the direction from which fluid flows, and“downstream” refers to the direction to which fluid flows. As used herein,“vertical” refers to a direction perpendicular to the ground. As used herein,“horizontal” refers to a direction parallel to the centerline of the turbofan 100. As used herein,“lateral” refers to a direction perpendicular to the axial vertical direction (e.g., the plane of entry and exit of the turbofan 100). Figure 1 、 2 etc.).

[0018] Various terms are used herein to describe the orientation of features. As used herein, the orientation of features, forces, and moments are described with reference to the axial, radial, and circumferential directions of a vehicle associated with the features, forces, and moments. Typically, the drawings are labeled with a set of axes including an axial axis A, a radial axis R, and a circumferential axis C. Additionally or alternatively, the drawings are labeled with a set of axes including a roll axis R, a pitch axis P, and a yaw axis Y.

[0019] "Comprising" and "including" (and all forms and tenses thereof) are used herein as open-ended terms. Therefore, whenever a claim uses any form of "comprising" or "including" (e.g., including, comprising, having, etc.) in a preamble or in any type of claim statement, it should be understood that additional elements, terms, etc., may be present without exceeding the scope of the corresponding claim or statement. As used herein, the phrase "at least" is open-ended when used as a transitional term, for example, in the preamble of a claim, as are the terms "comprising" and "including". The term "and / or", when used, for example, in the form of A, B, and / or C, refers to any combination or subset of A, B, and C, such as (1) A alone, (2) B alone, (3) C alone, (4) A and B, (5) A and C, (6) B and C, and (7) A and B and C. As used herein in the context of describing structures, components, items, objects, and / or things, the phrase "at least one of A and B" is intended to refer to an implementation that includes (1) at least one A, (2) at least one B, and (3) at least one A and at least one B. Similarly, as used herein in the context of describing structures, components, items, objects, and / or things, the phrase "at least one of A or B" is intended to refer to an implementation that includes (1) at least one A, (2) at least one B, and (3) at least one A and at least one B. As used herein in the context of describing the conduct or execution of processes, instructions, actions, activities, and / or steps, the phrase "at least one of A and B" is intended to refer to an implementation that includes (1) at least one A, (2) at least one B, and (3) at least one A and at least one B. Similarly, as used herein in the context of describing the conduct or execution of processes, instructions, actions, activities and / or steps, the phrase “at least one of A or B” is intended to refer to an implementation that includes (1) at least one A, (2) at least one B, and (3) any one of at least one A and at least one B.

[0020] As used herein, singular references (e.g., “a,” “an,” “first,” “second,” etc.) do not exclude multiple entities. As used herein, the term “a” or “an” refers to one or more of that entity. The terms “a” (or “an”), “one or more,” and “at least one” are used interchangeably herein. Furthermore, although listed separately, multiple means, elements, or method operations may be implemented by, for example, a single unit or processor. Additionally, while individual features may be included in different examples or claims, these may be combined, and inclusion in different examples or claims does not imply that combining features is impractical and / or disadvantageous.

[0021] Gas turbine engines include one or more compressors. The compressors can produce high pressure air for mixing with fuel for combustion and to provide combustion gases. In some examples, the compressors can produce an amount of compressed air that exceeds an amount used to produce the combustion gases. In these examples, the excess compressed air (e.g., compressor discharge air) can be used for secondary operations, such as cooling of engine components, engine ice protection, pneumatic actuators, etc.

[0022] In some existing examples, compressor discharge air is directed toward cooling of engine components (e.g., high pressure turbine shroud). However, in these examples, while the compressor discharge air is directed toward the engine components (e.g., high pressure turbine shroud), the compressor discharge air is not contained near these components. As a result, the compressor discharge air can move radially outward away from the engine components (e.g., high pressure turbine shroud), thereby reducing the cooling effect.

[0023] In some existing examples, compressor discharge air containment structures are used to contain the flow of cooling air near engine components (e.g., high pressure turbine shroud). However, there are difficulties in maintaining a seal in such containment structures. For example, during engine operation (e.g., during transients), the containment structure can move (e.g., radially and / or axially) relative to the engine components (e.g., high pressure turbine shroud). Such movement of the containment structure can result in difficulties in maintaining a seal of the containment structure.

[0024] Examples disclosed herein can contain cooling air (e.g., compressor discharge air) near engine components (e.g., high pressure turbine shroud). The examples disclosed herein use sealing techniques that allow for relative movement and flexibility to maintain a seal around the cooling air. By allowing for relative movement and flexibility of the containment structure, the seal is maintained throughout engine operation.

[0025] Reference will now be made in detail to examples of the present disclosure, one or more examples of which are illustrated in the drawings. Each example is provided by way of explanation of the present disclosure and is not meant as a limitation of the present disclosure. In fact, it will be apparent to those skilled in the art that various modifications and variations can be made in the present disclosure without departing from the scope or spirit of the disclosure. For instance, features illustrated or described as part of one example, can be used with another example to yield a still further example. Thus, it is intended that the present disclosure covers such modifications and variations as come within the scope of the appended claims and their equivalents.

[0026] Figure 1 is a schematic cross-sectional view of an existing art turbofan gas turbine engine 100 (“turbofan 100”). As Figure 1As shown, the turbofan 100 defines a longitudinal or axial centerline axis 102 extending through it for reference. Typically, the turbofan 100 may include a core turbine 104 or a gas turbine engine located downstream of the fan section 106.

[0027] The core turbine 104 typically includes a generally tubular outer casing 108 (“turbine casing 108”) defining an annular inlet 110. The casing 108 may be formed from a single casing or multiple casings. The casing 108 surrounds, in series flow relationship, a compressor section having a supercharger or low-pressure compressor 112 (“LP compressor 112”) and a high-pressure compressor 114 (“HP compressor 114”), a combustion section 116, a turbine section having a high-pressure turbine 118 (“HP turbine 118”) and a low-pressure turbine 120 (“LP turbine 120”), and an exhaust section 122. A high-pressure shaft or spool 124 (“HP shaft 124”) drivesably connects the HP turbine 118 and the HP compressor 114. A low-pressure shaft or spool 126 (“LP shaft 126”) drivesably connects the LP turbine 120 and the LP compressor 112. The LP shaft 126 can also be coupled to the fan spool or shaft 128 (“fan shaft 128”) of the fan section 106. In some examples, the LP shaft 126 can be directly coupled to the fan shaft 128 (e.g., direct drive configuration). In alternative configurations, the LP shaft 126 can be coupled to the fan shaft 128 via a reduction gearbox 130 (e.g., indirect drive or gear drive configuration).

[0028] like Figure 1 As shown, fan section 106 includes a plurality of fan blades 132 coupled to and extending radially outward from fan shaft 128. An annular fan housing or nacelle 134 circumferentially surrounds at least a portion of fan section 106 and / or core turbine 104. Nacelle 134 is supported relative to core turbine 104 by a plurality of circumferentially spaced outlet guide vanes 136. Furthermore, a downstream section 138 of nacelle 134 may surround an outer portion of core turbine 104 to define a bypass airflow passage 140 therebetween.

[0029] like Figure 1As shown, air 142 enters an inlet portion 144 of the turbofan 100 during operation of the turbofan 100. A first portion 146 of the air 142 flows into a bypass airflow passage 140, while a second portion 148 of the air 142 flows into an inlet 110 of the LP compressor 112. One or more sequential stages of LP compressor stator vanes 150 and LP compressor rotor blades 152 coupled to the LP shaft 126 progressively compress the second portion 148 of the air 142 flowing through the LP compressor 112 en route to the HP compressor 114. Next, one or more sequential stages of HP compressor stator vanes 154 and HP compressor rotor blades 156 coupled to the HP shaft 124 further compress the second portion 148 of the air 142 flowing through the HP compressor 114. This provides compressed air 158 to the combustion section 116, where it is mixed with fuel and combusted to provide combustion gases 160.

[0030] The combustion gases 160 flow through the HP turbine 118, where one or more sequential stages of HP turbine stator vanes 162 and HP turbine rotor blades 164 coupled to the HP shaft 124 extract a first portion of kinetic and / or thermal energy from the combustion gases 160. This energy extraction supports operation of the HP compressor 114. The combustion gases 160 then flow through the LP turbine 120, where one or more sequential stages of LP turbine stator vanes 166 and LP turbine rotor blades 168 coupled to the LP shaft 126 extract a second portion of thermal and / or kinetic energy therefrom. This energy extraction causes the LP shaft 126 to rotate, thereby supporting operation of the LP compressor 112 and / or rotation of the fan shaft 128. The combustion gases 160 then exit the core turbine 114 through its exhaust section 122.

[0031] The core turbine 104 functions for similar purposes as the turbofan 100 and is exposed to similar environments in land-based gas turbines, turbojet engines (where the ratio of the first portion 146 of the air 142 to the second portion 148 of the air 142 is less than the ratio of the turbofan), and ductless fan engines (where the fan section 106 is absent the nacelle 134). In each of the turbofan engine, the turbojet engine, and the ductless engine, a reduction device (e.g., the reduction gear box 130) can be included between any of the shafts and spools. For example, the reduction gear box 130 can be disposed between the LP shaft 126 and the fan shaft 128 of the fan section 106.

[0032] Figure 2 An example core turbine 104 that can be implemented in the example turbofan 100 shown is illustrated. Figure 1 The example core turbine 104 is shown with respect to an axial centerline axis 102. As shown, the core turbine 104 includes the HP compressor 114 having a compressor casing 202. Figure 2 As shown, the core turbine 104 includes the HP compressor 114 having a compressor casing 202.Figure 2 The example core turbine 104 of FIG. 1 includes a combustion section 116 having a forward combustor case 204. The forward combustor case 204 is coupled to the compressor case 202 at a forward flange joint assembly 206. Figure 2 The example combustion section 116 of FIG. 1 includes an aft combustor case 208. The forward combustor case 204 is coupled to the aft combustor case 208 at an intermediate flange joint assembly 210. Figure 2 The example core turbine 104 of FIG. 1 includes a turbine case 212. The turbine case is coupled to the aft combustor case 208 at an aft flange joint assembly 214.

[0033] Figure 2 The example core turbine 104 of FIG. 1 includes a stator plenum 216. The stator plenum 216 is coupled to the aft combustor case 208 between the intermediate flange joint assembly 210 and the aft flange joint assembly 214. At a forward end of the stator plenum 216, the stator plenum 216 is coupled to the forward combustor case 204 and the aft combustor case 208 at the intermediate flange joint assembly 210. At an aft end of the stator plenum 216, the stator plenum 216 is coupled to the aft combustor case 208 at a slot joint assembly 218. The slot joint assembly 218 can couple the aft end of the stator plenum 216 to the aft combustor case 208 while allowing the stator plenum 216 to move (e.g., radially and / or axially). In some examples, a flange joint assembly (e.g., the intermediate flange joint assembly 210) can be located at the aft end of the stator plenum 216 and a slot joint assembly (e.g., the slot joint assembly 218) can be located at the forward end of the stator plenum 216.

[0034] The stator plenum 216 forms a plenum cavity 220 between the stator plenum 216 and the aft combustor case 208. A compressor discharge duct 222 is coupled to the stator plenum 216. The compressor discharge duct 222 delivers a cooling flow 224 (e.g., compressor discharge air, compressor off-take, etc.) to the plenum cavity 220 to cool turbine components (e.g., the HP turbine 118, the LP turbine 120, etc.). For example, during engine operation, one or more compressors (e.g., the LP compressor 112 and / or the HP compressor 114) produce compressed air (e.g., compressor off-take) that is not used for combustion by a combustor (e.g., the combustion section 116). For example, the compressed air can form some or all of the cooling flow 224. The cooling flow 224 (e.g., compressor discharge air, compressor off-take, etc.) travels to the plenum cavity 220 of the stator plenum 216 via the compressor discharge duct 222. The cooling flow 224 provides cooling from the stator plenum 216 to engine components (e.g., the HP turbine 118, the LP turbine 120, etc.). In some examples, a second source of the cooling flow 224 distinct from the compressor section (e.g., the LP compressor 112 and / or the HP compressor 114) can form some or all of the cooling flow 224.

[0035] Figure 3 Show Figure 2 The example cross-sectional side view of the stator gas chamber 216 shown is illustrated. For example, the example stator gas chamber 216 disclosed herein can be used... Figure 1 The turbine fan 100 is used for implementation. As described above, the example stator chamber 216 is coupled to the front burner housing 204 and the rear burner housing 208 via a central flange connector assembly 210 at the front end of the stator chamber 216. The example stator chamber 216 includes a chamber flange 302 for coupling the stator chamber 216 in the central flange connector assembly 210. The central flange connector assembly 210 includes a fastener 304 that provides means for coupling (e.g., fixing) the chamber flange 302 to the burner housing (e.g., the front burner housing 204 and / or the rear burner housing 208). The central flange connector assembly 210 forms a front seal for the stator chamber 216. For example, since the stator gas chamber 216 is connected to the front combustor housing 204 and the rear combustor housing 208 via the intermediate flange joint assembly 210, the cooling flow 224 is sealed in the gas chamber cavity 220 at the front of the stator gas chamber 216.

[0036] As described above, at the rear end of the stator chamber 216, the stator chamber 216 is connected to the afterburner housing 208 via a slotted connector assembly 218. The slotted connector assembly 218 includes a slotted flange 306. In the illustrated example, the slotted flange 306 is fixedly connected to the afterburner housing 208. The example slotted connector assembly 218 includes a chamber end slot 308. The chamber end slot 308 is the end of the stator chamber 216, configured to connect the stator chamber 216 to the slotted flange 306 in the slotted connector assembly 218. In the illustrated example, the chamber end slot 308 is formed at the rear end of the outer surface 324 of the stator chamber 216 by a thickened portion of the outer surface 324 (e.g., housing, outer wall, etc.). The slotted flange 306 forms a cavity 310 to receive the chamber end slot 308. The example cavity 310 is axially tapered in a direction away from the chamber end slot 308. Figure 3 The cavity 310 includes an angled portion 312. Figure 3 In the example, the angled portion 312 is located in the inner portion of cavity 310 (e.g., closer to the cavity). Figure 2 On the axial centerline (axis 102). Figure 3 The chamber end slot 308 includes a corresponding angled portion 314. At the slot connector assembly 218, the chamber end slot 308 is coupled to the slot flange 306 via an insertion cavity 310. In some examples, the stator chamber 216 is first assembled at the intermediate flange connector assembly 210, and then axially compressed (e.g., in…). Figure 2in the direction of the axial centerline axis 102) to allow the plenum end slot 308 to be inserted into the cavity 310 of the slot flange 306.

[0037] During insertion, the angled portion 314 of the plenum end slot 308 can slide along the angled portion 312 of the slot flange 306 to help insert and seat the plenum end slot 308 in the cavity 310. In some examples, the stator plenum 216 remains axially compressed after assembly (e.g., during engine operation). In other words, the stator plenum 216 can be spring-loaded between the plenum flange 302 and the plenum end slot 308. The slot joint assembly 218 forms a rear seal of the stator plenum 216. For example, because the stator plenum 216 is coupled to the rear combustor case 208 via the slot joint assembly 218, the cooling flow 224 is sealed within the plenum cavity 220 at the rear of the stator plenum 216.

[0038] Figure 3 The stator plenum 216 is coupled to the compressor discharge pipe 222. The compressor discharge pipe 222 provides for the transfer of the cooling flow 224 from a source (e.g., the LP compressor 112 and / or the HP compressor 114) to the stator plenum 216. Cooling flow inlets 316 in the outer surface 324 of the stator plenum 216 provide fluid communication between the compressor discharge pipe 222 and the cavity 220 of the stator plenum 216. For example, during engine operation, the compressor section (e.g., the LP compressor 112 and / or the HP compressor 114) can produce excess compressed air that is not used for combustion. The excess compressed air (e.g., compressor exhaust) travels as the cooling flow 224 via the compressor discharge pipe 222. The cooling flow 224 (e.g., compressor exhaust) enters the cavity 220 of the stator plenum 216 via the cooling flow inlets 316.

[0039] Figure 3 The rear combustor case 208 shown in FIG. 1 includes a plurality of openings 318. The plurality of openings 318 allow for fluid communication between the cavity 220 and portions of the engine located inside (e.g., closer to the axial centerline axis 102) of the stator plenum 216. In some examples, the stator plenum 216 is located outside of the HP turbine 118 (e.g., further away from the axial centerline axis 102). In other examples, the stator plenum 216 is located outside of the LP turbine 120. In other examples, the stator plenum 216 is located outside of both the HP turbine 118 and the LP turbine 120. For example, the cooling flow 224 can travel from the cavity 220 through the openings 318 to the shroud of the HP turbine 118 and / or the shroud of the LP turbine 120. In this example, the cooling flow 224 can provide cooling for the HP turbine 118 and / or the LP turbine 120. Figure 2 Figure 2

[0040] ​​In some examples, the openings 318 are selectively positioned to provide cooling flow to and / or control the rate of cooling flow to one or more engine components. For example, a high density of one or more openings 318 can be located near the aft portion of the stator plenum 216 (e.g., outside of the LP turbine 120) to selectively provide cooling flow to the LP turbine 120. In Figure 3 In the illustrated example of FIG. 3, each opening 318 has a diameter that is substantially (e.g., within 10%) the same size. In other examples, each opening 318 can have a different diameter. In some examples, the diameter of the openings 318 can be selectively sized to control the rate of cooling flow to one or more engine components. For example, the openings 318 can be uniformly distributed from the forward portion of the stator plenum 216 to the aft portion of the stator plenum 216. However, a first plurality of openings 318 near the forward portion of the stator plenum 216 can have a smaller (e.g., 50% smaller) diameter than a second plurality of openings 318 near the aft portion of the stator plenum 216. In this example, the turbine components inside the aft portion of the stator plenum 216 can receive a higher amount or rate of cooling flow than the turbine components inside the forward portion of the stator plenum 216.

[0041] During operation of the turbine fan 100, the cavity 220 formed by the example stator plenum 216 can be subjected to high air pressure conditions. For example, the flow rate of the cooling flow 224 entering the cavity 220 can be significantly (e.g., 30%) higher than the flow rate of the cooling flow 224 exiting the cavity 220 (e.g., through the openings 318). In particular, the high pressure conditions of the cavity 220 can occur during transient (e.g., non-steady state) operation of the turbine fan 100. During the high pressure conditions, the air pressure within the cavity 220 exhibits a load on the stator plenum 216. If the stator plenum 216 is fixedly coupled to the combustor case 208, the load caused by the high pressure conditions can cause stator plenum failure (e.g., material rupture, seal failure, etc.). Accordingly, it is desirable to configure the stator plenum 216 such that the stator plenum 216 is not fixedly coupled. In other words, it is desirable to configure one or more joints of the stator plenum 216 (e.g., the intermediate flange joint assembly 210 and / or the slotted joint assembly 218) such that the stator plenum 216 is allowed to move (e.g., radially and / or axially) while maintaining the forward and aft seals.

[0042] Accordingly, Figure 3The slot joint assembly 218 shown in the middle is configured to allow the stator plenum 216 to move (e.g., radially and / or axially) while maintaining the back seal. The angled portion 312 of the slot flange 306 is adjacent to the angled portion 314 of the plenum end slot 308. When assembling the stator plenum 216 to the turbofan 100, the frictional force between the angled portion 312 and the angled portion 314 maintains the position of the plenum end slot 308 within the cavity 310. Under steady state conditions, a space 320 is formed between the end of the plenum end slot 308 and the slot flange 306. During high air pressure conditions when air pressure loads the stator plenum 216, the plenum end slot 308 can displace (e.g., move) within the cavity 310 of the slot flange 306 due to the space 320 and the angled portions 312, 314. However, the second seal is maintained when the plenum end slot 308 is displaced within the cavity 310. Because the slot joint assembly 218 allows the stator plenum 216 to move, the front joint (e.g., the intermediate flange joint assembly 210) of the stator plenum 216 can be a fixed coupling that maintains the first seal during all operating conditions. Thus, the stator plenum 216 can move (e.g., radially and / or axially) during operation of the turbofan 100 while maintaining the first seal and the second seal.

[0043] As described above, the stator plenum 216 can be axially compressed for installation and can maintain an axial load during engine operation to maintain the first seal and the second seal. Further, during engine operation, the axial load on the stator plenum 216 can increase, for example, during transient (e.g., non-steady state) operation. If the stator plenum 216 is exposed to a long term or excessive axial load (e.g., an axial load above a threshold value), the stator plenum 216 can fail (e.g., material rupture, seal failure, etc.). To reduce the axial force experienced by the stator plenum 216, the stator plenum 216 includes a flexible portion 322. The flexible portion 322 is located between the front end of the stator plenum 216 and the back end of the stator plenum 216. The flexible portion 322 is formed by one or more bends in an outer surface 324 of the stator plenum 216. The flexible portion 322 forms a cavity 326. The cavity 326 is a portion of the plenum cavity 220. When the stator plenum 216 is subjected to an axial force, the flexible portion 322 can provide a location along the outer surface 324 for elastic deformation of the stator plenum 216. The elastic deformation can reduce the axial load experienced by the stator plenum 216. Thus, the flexible portion 322 can reduce the axial load experienced by the stator plenum 216.

[0044] Further, the flexible portion 322 can provide a location along the outer surface 324 for elastic deformation of the stator plenum 216 during installation. For example, after installation of the plenum flange 302 within the mid-flange joint assembly 210, the stator plenum 216 can be compressed via elastic deformation at the flexible portion 322 in order to insert the plenum end slot 308 into the cavity 310 of the slot flange 306. Further, the flexible portion 322 can be configured to minimize or otherwise reduce aerodynamic drag along the outer surface 324 of the stator plenum 216. The flexible portion 322, and thus the cavity 326, can have different shapes as shown below in Figure 4 and Figure 5 .

[0045] Figure 4 An example cross-sectional side view of a second example stator plenum 400 is shown. The second example stator plenum 400 disclosed herein can be implemented with the turbofan 100 of Figure 1 and / or the core turbine 104 of Figure 2 . The second example stator plenum 400 includes a flexible portion 402 forming a cavity 404. Figure 4 The flexible portion 402 of the example stator plenum 400 has a different shape than the flexible portion 322 of the example stator plenum 216 of Figure 2 and / or Figure 3 . As a result, Figure 4 The cavity 404 of the example stator plenum 400 has a different shape than the cavity 326 of the example stator plenum 216 of Figure 2 and / or Figure 3 . Figure 4 The flexible portion 402 of the stator plenum 400 can have different properties (e.g., aerodynamic drag, elastic deformation properties) than the flexible portion 322 of the stator plenum 216 of Figure 2 and / or Figure 3 . The example stator plenum 400 includes a plenum end slot 308 coupled to the slot flange 306.

[0046] Figure 5 An example cross-sectional side view of a third example stator plenum 500 is shown. The third example stator plenum 500 disclosed herein can be implemented with the turbofan 100 of Figure 1 and / or the core turbine 104 of Figure 2 . The second example stator plenum 500 includes a flexible portion 502 forming a cavity 504. Figure 5 The flexible portion 502 of the example stator plenum 500 has a different shape than the flexible portion 322 of the example stator plenum 216 of Figure 2 and / or Figure 3 and the flexible portion 402 of the example stator plenum 400 of Figure 4 . As a result, Figure 5the cavity 504 of the example stator plenum 500 has a different shape than Figure 2 and / or Figure 3 the cavity 326 of the example stator plenum 216 of Figure 4 the cavity 404 of the example stator plenum 400. Figure 5 the flexible portion 502 of the stator plenum 500 can have different properties (e.g., aerodynamic drag, elastic deformation properties) than Figure 4 the flexible portion 402 of the example stator plenum 400 and / or Figure 2 and / or Figure 3 the flexible portion 322 of the stator plenum 216. The example stator plenum 500 includes a plenum end slot 308 coupled to the slot flange 306.

[0047] Figure 6 An example cross-sectional side view of a fourth example stator plenum 600 is shown. The fourth example stator plenum 600 disclosed herein can be implemented with Figure 1 the turbofan 100 and / or Figure 2 the core turbine 104. Figure 6 The example stator plenum 600 includes a flexible portion 402 forming a cavity 404. In Figure 6 the example, the slot joint assembly 602 includes a slot flange 604 and a plenum end slot 606. The slot flange 604 is coupled to the combustor case 208. The slot flange 604 forms a cavity 608. The cavity 608 includes an angled portion 610. In Figure 6 the example, the angled portion 610 is located on an inner portion (e.g., closer to Figure 2 the axial centerline axis 102) of the cavity 608. Figure 6 The plenum end slot 606 does not include an angled portion corresponding to the angled portion 610 of the slot flange 604. The slot flange 604 includes a space 612. In Figure 6 the example, the space 612 is located between a rear end of the plenum end slot 606 and a front surface of the cavity 608.

[0048] Figure 7 An example cross-sectional side view of a fifth example stator plenum 700 is shown. The fifth example stator plenum 70 disclosed herein can be implemented with Figure 1 the turbofan 100 and / or Figure 2 the core turbine 104. Figure 7 The example stator plenum 700 includes a flexible portion 402 forming a cavity 404. In Figure 7 the example, the slot joint assembly 702 includes a slot flange 704 and a plenum end slot 706. The slot flange 704 is coupled to the combustor case 208. The slot flange 704 forms a cavity 708. The cavity 708 includes an angled portion 710. In Figure 7In the example, the angled portion 710 is located on the outer portion of cavity 708 (e.g., away from it). Figure 2 On the axial centerline (axis 102). Figure 6 The air chamber end slot 706 includes a corresponding angled portion 712. The slot flange 704 includes a space 714. Figure 7 In the example, space 714 is located between the rear end of the air chamber end slot 706 and the inner surface of cavity 708.

[0049] Stator chambers 216, 400, 500, 600, and / or 700 can be combined, separated, rearranged, etc. For example, flexible portions 322, 402, and 502 can be combined with any of the chamber end slots 308, 606, and 706. In some examples, the flexible portions of stator chambers 216, 400, 500, 600, and 700 can change shape along the circumference of the stator chamber. Additionally or alternatively, the chamber end slots of stator chambers 216, 400, 500, 600, and 700 can change shape along the circumference of the stator chamber.

[0050] Stator chambers 216, 400, 500, 600, and / or 700 can provide cooling for engine components during engine operation. At least stator chambers 216, 400, 500, 600, and 700 can be equipped with means for receiving cooling flow. A notch flange 306 can provide means for connecting stator chambers 216, 400, 500, 600, and 700 to the engine housing. In some examples, the connection is a non-fixed connection, such as a ball joint, pivot joint, etc. The notch flange 306 can provide means for sealing stator chambers 216, 400, 500, 600, and 700 to the engine housing. At least chamber end notches 308, 606, and 706 can be equipped with means for connecting stator chambers 216, 400, 500, 600, and 700 to the engine housing. At least the chamber end slots 308, 606, 706 and / or slot flanges 306, 604, 704 may be implemented with means for sealing the stator chambers 216, 400, 50, 600, 700 to the engine housing. At least the chamber end slots 308, 606, 706 and / or slot flanges 306, 604, 704 may be implemented with means for allowing the stator chambers 216, 400, 50, 600, 700 to move while maintaining a seal. Flexible portions 322, 402, 502 may provide means for reducing axial loads on the stator chambers 216, 400, 500, 600, 700.

[0051] “Comprise,” “comprising,” and “comprises” and “comprising” (and all forms of these terms) are used herein as open-ended terms. Thus, whenever a claim employs any form of “comprising” (e.g., “comprise,” “comprising,” “comprises,” “include,” “including,” “includes,” “contain,” “containing,” “contains,” etc.), it should be interpreted as including additional elements, terms, etc. that are not expressly recited in the claim. As used herein, the phrase “at least” as used, e.g., as the transitional term in a claim, is open-ended, as is the term “comprising” and “including.” The term “and / or” when used in the form “A, B, and / or C” means A, B, C individually or any combination or subset thereof, e.g., (1) A alone, (2) B alone, (3) C alone, (4) A and B together, (5) A and C together, (6) B and C together, or (7) A, B, and C together. As used herein in the context of describing structural, component, item, object, and / or thing, the phrase “at least one of A and B” is intended to refer to implementations that include (1) at least one A, (2) at least one B, or (3) any of A and at least one B. Similarly, as used herein in the context of describing structural, component, item, object, and / or thing, the phrase “at least one of A or B” is intended to refer to implementations that include (1) at least one A, (2) at least one B, or (3) any of A and at least one B. As used herein in the context of describing performance or execution of processes, instructions, actions, activities, and / or steps, the phrase “at least one of A and B” is intended to refer to implementations that include (1) at least one A, (2) at least one B, or (3) any of A and at least one B. Similarly, as used herein in the context of describing performance or execution of processes, instructions, actions, activities, and / or steps, the phrase “at least one of A or B” is intended to refer to implementations that include (1) at least one A, (2) at least one B, or (3) any of A and at least one B.

[0052] As used herein, singular references (e.g., “a,” “an,” “the,” “first,” “second,” etc.) do not exclude multiple. As used herein, the term “a” or “an” object refers to one or more of the object. The terms “a” (or “an”), “one or more”, and “at least one” are used interchangeably herein. Furthermore, although individually listed, a plurality of devices, elements or method actions can be implemented by, e.g., a single entity or object. Additionally, although individual features can be included in different examples or claims, these can possibly be combined, and the inclusion of such features in different examples or claims does not imply that a combination of features is not feasible and / or advantageous.

[0053] From the foregoing, it will be appreciated that the above- disclosed methods, apparatus, and articles of manufacture have been disclosed to provide improved cooling of engine components of a gas turbine engine. The disclosed methods, apparatus, and articles of manufacture provide a containment structure for a cooling flow. The containment structure improves cooling of a gas turbine engine by directing a cooling flow to one or more engine components while preventing the cooling flow from escaping to an external space, such as a bypass airflow region. Improving cooling of engine components can increase engine efficiency and reduce engine component wear due to thermal loading. Examples disclosed herein provide a combination of fixed couplings and non-fixed couplings and selectively flexible structures to allow containment of a cooling flow without failure of a seal forming a containment space or containment structure itself.

[0054] Disclosed herein are example methods, apparatus, systems, and articles of manufacture implementing a stator plenum with collet seals. Further examples and combinations thereof include the following: Example 1 includes a stator plenum for a gas turbine engine, the stator plenum comprising: an outer shell surrounding a centerline axis; a first end of the outer shell coupled to an engine casing at a first coupling, the first coupling forming a first seal; a second end of the outer shell coupled to the engine casing at a second coupling, the second end formed by a thickened portion of the outer shell, the second coupling forming a second seal; and a cavity formed by the outer shell, the cavity containing a cooling flow to reduce a temperature of a turbine.

[0055] Example 2 includes the stator plenum of Example 1, wherein the first coupling is a fixed coupling and the second coupling is a non-fixed coupling.

[0056] Example 3 includes the stator plenum of Example 1, further comprising a flexible portion of the outer shell to reduce an axial load on the stator plenum.

[0057] Example 4 includes the stator plenum of Example 3, wherein the flexible portion is formed by one or more bends in the outer shell.

[0058] Example 5 includes the stator plenum of Example 1, wherein the first coupling is formed via a fastener.

[0059] Example 6 includes the stator plenum of Example 1, wherein the engine casing comprises an annular flange having a second cavity to receive the second end of the stator plenum.

[0060] Example 7 includes the stator plenum of Example 6, wherein the second coupling is formed by the second end of the stator plenum inserted into the second cavity.

[0061] Example 8 includes the stator plenum of Example 1, wherein the second end comprises a friction angle.

[0062] Example 9 includes the stator plenum of Example 1, wherein the stator plenum is axially compressed between the first end and the second end.

[0063] Example 10 includes the stator plenum of Example 9, wherein the axial compression provides a seal for the second seal.

[0064] Example 11 includes the stator plenum of Example 1, wherein the cooling flow is compressor discharge air.

[0065] Example 12 includes a gas turbine engine, comprising: a compressor; a combustion section; an engine case, the engine case comprising a first cavity; a turbine; a shaft rotatably coupling the compressor and the turbine; and a stator plenum, the stator plenum comprising: an outer shell surrounding a centerline axis; a first end of the outer shell coupled to the engine case at a first coupling, the first coupling forming a first seal; a second end of the outer shell received within the first cavity of the engine case at a second coupling, the second coupling forming a second seal; and a second cavity formed by the outer shell, containing a cooling flow to reduce a temperature of the turbine.

[0066] Example 13 includes the gas turbine engine of Example 12, wherein the first cavity is axially tapered away from the second end.

[0067] Example 14 includes the gas turbine engine of Example 12, wherein the second end is axially tapered toward the first cavity.

[0068] Example 15 includes the gas turbine engine of Example 12, wherein the first end is fixedly coupled to the engine case and the second end is non-fixedly coupled to the engine case.

[0069] Example 16 includes the gas turbine engine of Example 12, further comprising a flexible portion of the outer shell to reduce an axial load on the stator plenum.

[0070] Example 17 includes the gas turbine engine of Example 12, wherein the engine case comprises an opening to allow the cooling flow to travel from the cavity to the turbine.

[0071] Example 18 includes the gas turbine engine of Example 17, wherein the opening comprises a first portion having a first diameter and a second portion having a second diameter.

[0072] Example 19 includes the gas turbine engine of Example 12, wherein the cooling flow is discharge air from the compressor.

[0073] Example 20 includes an apparatus for cooling a gas turbine engine, the apparatus comprising: a means for containing a cooling flow; a means for fixedly coupling a first end of the means for containing to an engine case; a means for non-fixedly coupling a second end of the means for containing to the engine case; and a means for reducing an axial load on the means for containing a cooling flow.

[0074] Although certain example systems, methods, apparatus, and articles of manufacture have been disclosed herein, the scope of coverage of this patent is not limited thereto. On the contrary, this patent covers all systems, methods, apparatus, and articles of manufacture falling within the scope of the claims.

[0075] The following claims are hereby incorporated into this detailed description by reference, in which each claim stands as a separate embodiment of this disclosure.

Claims

1. A stator plenum for a gas turbine engine, characterized by, The stator plenum comprises: an outer shell about a centerline axis; an engine casing about the centerline axis, wherein the engine casing is positioned between the outer shell and the centerline axis in a radial direction defined by the gas turbine engine, wherein the engine casing comprises a flange defining a first cavity; a first end of the outer shell coupled to the engine casing at a first coupling, the first coupling forming a first seal; a second end of the outer shell coupled to the engine casing at a second coupling, the second end formed by a thickened portion of the outer shell, wherein the thickened portion is positioned at least partially in the first cavity, wherein a space is defined between the second end and the flange, wherein the thickened portion is movable into the space during operation of the gas turbine engine, the second coupling forming a second seal, wherein the first coupling is a fixed coupling and the second coupling is a non-fixed coupling; a second cavity formed between the engine casing and the outer shell, the second cavity containing a cooling flow to reduce a temperature of a turbine; and a flexible portion of the outer shell that reduces an axial load on the stator plenum.

2. The stator plenum of claim 1, wherein, wherein the flexible portion is formed by one or more bends in the outer shell.

3. The stator plenum of claim 1, wherein, wherein the first coupling is formed via a fastener.

4. The stator plenum of claim 1, wherein, wherein the flange is an annular flange.

5. The stator plenum of claim 4, wherein, wherein the second coupling is formed by the second end of the outer shell inserted into the first cavity.

6. The stator plenum of claim 1, wherein, wherein the second end comprises a friction angle.

7. The stator plenum of claim 1, wherein, wherein the outer shell is axially compressed between the first end and the second end.

8. The stator plenum of claim 7, wherein, wherein the axial compression provides a seal for the second seal.

9. The stator plenum of claim 1, wherein, wherein the cooling flow is compressor discharge air.

10. A gas turbine engine characterized by, Comprising: a compressor; a combustion section; an engine casing comprising a flange defining a first cavity; a turbine; a shaft rotatably coupling the compressor and the turbine; and a stator plenum comprising: an outer shell about a centerline axis, wherein a second cavity is formed between the engine casing and the outer shell to contain a cooling flow to reduce a temperature of the turbine; a first end of the outer shell coupled to the engine casing at a first coupling, the first coupling forming a first seal, wherein the first coupling is a fixed coupling; a second end of the outer shell received within the first cavity of the engine casing at a second coupling, the second end formed by a thickened portion of the outer shell, wherein the thickened portion is positioned at least partially in the first cavity, wherein a space is defined between the second end and the flange, wherein the thickened portion is movable into the space during operation of the gas turbine engine, the second coupling forming a second seal, wherein the second coupling is a non-fixed coupling; and a flexible portion of the outer shell that reduces an axial load on the outer shell.

11. The gas turbine engine of claim 10, wherein, wherein the first cavity is axially tapered away from the second end.

12. The gas turbine engine of claim 10, wherein, wherein the second end is axially tapered toward the first cavity.

13. The gas turbine engine of claim 10, wherein, wherein the first end of the outer shell is fixedly coupled to the engine casing and the second end of the outer shell is non-fixedly coupled to the engine casing.

14. The gas turbine engine of claim 10, wherein, wherein the engine casing includes an opening to allow the cooling flow to travel from the second cavity to the turbine.

15. The gas turbine engine of claim 14, wherein, wherein the opening includes a first portion having a first diameter and a second portion having a second diameter.

16. The gas turbine engine of claim 10, wherein, wherein the cooling flow is discharge air from the compressor.

17. An apparatus for cooling a gas turbine engine, comprising: The apparatus comprises: means for containing a cooling flow; means for fixedly coupling a first end of the means for containing to an engine casing, the means for fixedly coupling forming a first seal; means for non-fixedly coupling a second end of the means for containing to the engine casing; means for allowing the means for containing a cooling flow to move while maintaining a second seal at the means for non-fixedly coupling via a friction force at the second end; and means for enabling elastic deformation of the means for containing during installation when the means for fixedly coupling is coupled to the engine casing and the means for non-fixedly coupling is not coupled to the engine casing, wherein the means for enabling elastic deformation enables the means for containing to be compressed in an axial direction and subsequently decompressed in the axial direction during installation.

18. The apparatus of claim 17, wherein, The means for non-fixedly coupling is formed by a thickened portion of the means for containing.

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