EP4671611A1

EP4671611A1 - Combustion chamber wall soil reduction for gas turbine bee engine

Info

Publication number: EP4671611A1
Application number: EP25185338.8A
Authority: EP
Inventors: Stephan Kramer; Ryan LUNDGREEN; Dibesh JOSHI; Gregory Boardman; Kyle MCFERRAN; Karen THOLE
Original assignee: RTX Corp
Current assignee: RTX Corp
Priority date: 2024-06-25
Filing date: 2025-06-25
Publication date: 2025-12-31

Abstract

A combustor (56) has a combustor shell (104; 184) defining a plurality of first impingement holes (105), a particle collection panel (120) defining a plurality of second impingement holes (105) and disposed inward of the combustor shell (104; 184), and a combustor panel (110) defining a plurality of effusion holes (107) and disposed inward of the particle collection panel (120). The particle collection panel (120) includes a plurality of raised cooling features (122) disposed on an outward surface of the particle collection panel (120). The plurality of raised cooling features (122) are configured to promote heat transfer and to collect and/or entrap particulate matter from cooling air flowing through the combustor (56) when the combustor (56) is in operation and each of the plurality of raised cooling features (122) extends outward from an outward surface of the particle collection panel (120).

Description

CROSS-REFERENCE TO RELATED APPLICATIONS

This application claims the benefit of US Provisional Application 63/663,887 filed June 25, 2024 for "Gas Turbine Engine Combustor Wall Dirt Mitigation," the disclosure of which is incorporated its entirety in into this application by reference.

GOVERNMENT RIGHTS

This invention was made with government support under FAA Award Number 13866648 awarded by the US Federal Aviation Administration Office of Environment and Energy. The government has certain rights in the invention.

TECHNICAL FIELD

The present disclosure relates to combustors, and more specifically, to capturing particles from cooling air in a combustor of a gas turbine engine.

BACKGROUND

A gas turbine engine typically includes a fan section, a compressor section, a combustor section, and a turbine section. A fan section may drive air along a bypass flowpath while a compressor section may drive air along a core flowpath. In general, during operation, air is pressurized in the compressor section and is mixed with fuel and burned in the combustor section to generate hot combustion gases. The hot combustion gases flow through the turbine section, which extracts energy from the hot combustion gases to power the compressor section and other gas turbine engine loads. The compressor section typically includes low pressure and high pressure compressors, and the turbine section includes low pressure and high pressure turbines.
Combustors used in gas turbine engines generally rely on combustor panels, attached to a combustor shell (also known as a combustor liner), to interface with hot combustion gases and guide the combustion gases into the turbine. Cooling air generally flows from a diffuser chamber through impingement holes of the combustor shell and then flows through the combustor panel via effusion holes into the combustion chamber. However, dirt, debris, sand, and/or other particulate matter entrained with the cooling airflow, if allowed to enter the combustion chamber, can have an adverse effect on the operational life, efficiency, and performance of the combustor.

SUMMARY

One aspect of this disclosure is directed to a combustor having a combustor shell defining a plurality of first impingement holes, a particle collection panel defining a plurality of second impingement holes and disposed inward of the combustor shell, and a combustor panel defining a plurality of effusion holes and disposed inward of the particle collection panel. The particle collection panel includes a plurality of raised cooling features disposed on an outward surface of the particle collection panel. The plurality of raised cooling features are configured to promote heat transfer and to collect and/or entrap particulate matter from cooling air flowing through the combustor when the combustor is in operation and each of the plurality of raised cooling features extends outward from an outward surface of the particle collection panel.
Another aspect of this disclosure is directed to a gas turbine engine including a combustor having a combustor shell defining a plurality of first impingement holes, a particle collection panel defining a plurality of second impingement holes and disposed inward of the combustor shell, and a combustor panel defining a plurality of effusion holes and disposed inward of the particle collection panel. The particle collection panel includes a plurality of raised cooling features disposed on an outward surface of the particle collection panel. The plurality of raised cooling features are configured to promote heat transfer and to collect and/or entrap particulate matter from cooling air flowing through the combustor when the combustor is in operation and each of the plurality of raised cooling features extends outward from an outward surface of the particle collection panel.

BRIEF DESCRIPTION OF THE DRAWINGS

Fig. 1 is a cross-sectional view of an exemplary gas turbine engine.
Fig. 2 is a cross-sectional view of an exemplary combustor of a gas turbine engine.
Fig. 3A is a cross-sectional view of a combustor of a gas turbine engine.
Fig. 3B is a cross-sectional view of a combustor of a gas turbine engine.
Fig. 3C is a cross-sectional view of a combustor of a gas turbine engine showing exploded views (a), (b), and (c) of raised cooling features of the present disclosure.

DETAILED DESCRIPTION

In various embodiments and with reference to Fig. 1, a gas turbine engine 20 is provided. Gas turbine engine 20 may be a two-spool turbofan that generally incorporates a fan section 22, a compressor section 24, a combustor section 26, and a turbine section 28. Alternative engines may include, for example, an augmentor section among other systems or features. In operation, fan section 22 can drive coolant (e.g., air) along a bypass flow-path B while compressor section 24 can drive coolant along a core flow-path C for compression and communication into combustor section 26 then expansion through turbine section 28. Although Fig. 1 depicts a turbofan gas turbine engine 20 it should be understood that the concepts described in this disclosure are not limited to use with turbofan engines as the teachings may be applied to other types of turbine engines including three-spool architectures.
Gas turbine engine 20 may generally include a low speed spool 30 and a high speed spool 32 mounted for rotation about an engine central longitudinal axis A-A' relative to an engine static structure 36 or engine case via several bearing systems 38, 38-1, and 38-2. Engine central longitudinal axis A-A' is oriented in the z direction on the provided xyz axis. It should be understood that various bearing systems 38at various locations may alternatively or additionally be provided, including for example, bearing system 38, bearing system 38-1, and bearing system 38-2.
Low speed spool 30 may generally include an inner shaft 40 that interconnects a fan 42, a low pressure compressor 44, and a low pressure turbine 46. Inner shaft 40 may be connected to fan 42 through a geared architecture 48 that can drive fan 42 at a lower speed than low speed spool 30. Geared architecture 48 may include a gear assembly 60 enclosed within a gear housing 62. Gear assembly 60 couples inner shaft 40 to a rotating fan structure. High speed spool 32 may include an outer shaft 50 that interconnects a high pressure compressor 52 and high pressure turbine 54.
A combustor 56 may be located between high pressure compressor 52 and high pressure turbine 54. The combustor section 26 may have an annular wall assembly having inner and outer shells that support respective inner and outer heat shielding liners. The heat shield liners may include a plurality of combustor panels that collectively define the annular combustion chamber of the combustor 56. An annular cooling cavity is defined between the respective shells and combustor panels for supplying cooling air. Impingement holes are located in the shell to supply the cooling air from an outer air plenum and into the annular cooling cavity.
A mid-turbine frame 57 of engine static structure 36 may have a mid-turbine vane 59 and may be located generally between high pressure turbine 54 and low pressure turbine 46. Mid-turbine frame 57 may support one or more bearing systems 38 in turbine section 28. Inner shaft 40 and outer shaft 50 may be concentric and rotate via bearing systems 38 about the engine central longitudinal axis A-A', which is collinear with their longitudinal axes. As used in this disclosure, a "high pressure" compressor or turbine experiences a higher pressure than a corresponding "low pressure" compressor or turbine.
The core airflow C may be compressed by low pressure compressor 44 then by high pressure compressor 52, mixed and burned with fuel in combustor 56, then expanded over high pressure turbine 54 and low pressure turbine 46. Turbines 46, 54 rotationally drive the respective low speed spool 30 and high speed spool 32 in response to the expansion.
In various embodiments, geared architecture 48 may be an epicyclic gear train, such as a star gear system (sun gear in meshing engagement with a plurality of star gears supported by a carrier and in meshing engagement with a ring gear) or other gear system. Geared architecture 48 may have a gear reduction ratio of greater than about 2.3 and low pressure turbine 46 may have a pressure ratio that is greater than about 5. In various embodiments, the bypass ratio of gas turbine engine 20 is greater than ten (10:1). In various embodiments, the diameter of fan 42 may be significantly larger than that of the low pressure compressor 44, and the low pressure turbine 46 may have a pressure ratio that is greater than five (5:1). Low pressure turbine 46 pressure ratio may be measured prior to inlet of low pressure turbine 46 as related to the pressure at the outlet of low pressure turbine 46 prior to an exhaust nozzle. It should be understood, however, that the above parameters are exemplary of various embodiments of a suitable geared architecture engine and that the present disclosure contemplates other gas turbine engines including direct drive turbofans. A gas turbine engine may include an industrial gas turbine (IGT) or a geared aircraft engine, such as a geared turbofan, or non-geared aircraft engine, such as a turbofan, or may include any gas turbine engine as desired.
With reference to Fig. 2, an in accordance with various embodiments, one or more combustor panels 110 (e.g., thermal shields, combustor liners) may be positioned in combustor 56 to protect various features of the combustor 56 from the high temperature flames and/or combustion gases. The combustor 56, in various embodiments, may have a combustor chamber 102 defined by a combustor outer shell 104 and a combustor inner shell 184. A diffuser chamber 101 is external the combustor 56 and cooling air may be configured to flow through the diffuser chamber 101 around the combustor 56. The combustor chamber 102 may include a region of mixing of core airflow C (see Fig. 1) and fuel, and may direct the high-speed exhaust gases produced by the ignition of this mixture inside the combustor 56. The combustor outer shell 104 and the combustor inner shell 184 may provide structural support to the combustor 56 and its components. For example, a combustor outer shell 104 and a combustor inner shell 184 may include a substantially cylindrical or a substantially conical canister portion defining an inner area comprising the combustor chamber 102.
As mentioned above, it may be desirable to protect the combustor outer shell 104 (also known as a combustor outer liner) and the combustor inner shell 184 (also known as a combustor inner liner) from the harmful effects of high temperatures. Accordingly, one or more combustor panels 110 may be disposed inside the combustor chamber 102 to provide such protection and may be mounted to the combustor chamber 102 using one or more attachment features 106. The combustor panels 110 may include a partial cylindrical or conical surface section. An outer combustor thermal panel may be arranged radially inward of the combustor outer shell 104, for example, circumferentially about the inner surface of the combustor outer shell 104 and one or more inner combustor panels may also be arranged radially outward of the combustor inner shell 184. Thus, while the terms "radially outward" and "radially inward" are defined above as being relative to the engine central longitudinal axis A-A', the terms "outward" and "inward," without the modifier "radially", refer to positions relative to the combustor chamber 102. That is, the combustor shells 104, 184 are outward of the combustor panels 110, and vice versa. The combustor panels 110 may be made from a variety of materials, such as metal, metal alloys, and/or ceramic matrix composites, among others.
With reference to Figs. 3A, 3B, and 3C, an annular cooling cavity 117 is formed and/or defined between the combustor shell 104, which for purposes of this disclosure will be alternately referred to a first impingement plate 104, and the combustor panel 110, which for purposes of this disclosure will also be referred to as effusion plate 110. As mentioned above, cooling air in the diffuser chamber 101 may enter the annular cooling cavity 117 via impingement holes 105 formed in the combustor shell 104. That is, impingement holes 105 may extend from a diffuser-facing side 141 of the combustor shell 104 to a combustor-facing side 142 of combustor shell 104 and may supply cooling air to the annular cooling cavity 117. The cooling air in the annular cooling cavity 117 may enter the combustor chamber 102 via effusion holes 107 formed in the combustor panel. That is, effusion holes 107 may extend from a cooling surface or "cold side" 131 of the combustor panel to a combustion facing surface or "hot side" 132 of the combustor panel that is opposite the cold side 131. In various embodiments, the effusion holes 107 are generally oriented to create a protective "blanket" of air film over the hot side 132 of the combustor panel thereby protecting the combustor panel from the hot combustion gases in the combustor chamber 102.
A particle collection panel 120, which for purposes of this disclosure will be alternately referred to a second impingement plate 120, is disposed between the combustor shell 104 and the combustor panel 110 (e.g., in the annular cooling cavity 117). That is, the particle collection panel 120 may be inward of the combustor shell 104, and the combustor panel 110 is disposed inward of the particle collection panel 120. As shown in Fig. 3C, the particle collection panel 120 also includes a plurality of raised cooling features 122, which may be a plurality of pins 122(a) (see Fig. 3C(a)), a plurality of diamond fins 122(b) (see Fig. 3C(b)), a plurality of fence fins 122(c) (see Fig. 3C(c)), or any another geometry appropriate for a particular application. Each of plurality of pins 122(a) may be a cylindrical or similar pin-like structure (e.g., ellipsoidal, pyramidal, etc. structure) with dimensions and pin-to-pin spacing appropriate for a particular application. Each of the diamond fins 122(b) may be a raised structure having polygonal shape (e.g., a triangle, quadrilateral [diamond, rectangle, etc.], pentagon, etc.) with dimensions and fin-to-fin spacing appropriate for a particular application. Each of the raised fences 122(c) may be a fence-like structure (e.g., an elongated rectangular prism or similar structure) with dimensions and fence-to-fence spacing appropriate for a particular application. Each of the plurality of raised cooling features 122 extends outward from an outward surface of the particle collection panel 120 and form an extended heat transfer surface.
In some examples, the impingement holes 105 are arranged at a 90° angle to the surface of the impingement plate 120 (i.e., at a 180° angle ("in line") with respect to the cooling air flow). In some examples, the effusion holes 107 are angled at a 30° angle to the surface of the combustor panel 100 (i.e., at a 60° angle with respect to the cooling air flow). The impingement holes 105 and effusion holes 107 can have diameters of 1.5 mm (0.06 in.), 2.3 mm (0.09 in.), 3.2 mm (0.125 in.), or any other diameter deemed appropriate for a particular application. The quantity, diameter, and geometric arrangement of impingement holes 105 and effusion holes 107 on their respective plates can be any quantity, diameter, and geometric arrangement deemed appropriate for a particular application. Similarly, the quantity, height, and geometric arrangement of the raised cooling features 122 can be any quantity, height, a d geometric arrangement deemed appropriate for a particular application. In addition, the spacing between the combustor shell 104, the particle collection panel 120, and the combustor panel 110 can be any spacing deemed appropriate for a particular application.
The raised cooling features 122 are configured to promote heat transfer and to collect/entrap dirt, debris, sand, and/or other particulate matter from the cooling air. Collecting particles in the cooling air, such as dirt, debris, or other particulate matter, on the particle collection panel 120 and the raised cooling features 122 result in the cooling air downstream of the particle collection panel 120 having a substantial portion of the particles stripped from the cooling air. As a result, the cooling air is "cleaner" and thus well-suited to flow through a plurality of second impingement holes 125 defined in the particle collection panel 120 and through the effusion holes 107 defined in the combustor panel 110 into the combustion chamber 102. Said differently, the number of particles (e.g., the flux of particulate matter) reaching the combustion chamber 102 is reduced by incorporating the particle collection panel 120 between the combustor shell 104 and combustor panel 110. By removing or reducing the amount of particles that flow into the combustion chamber 102 via the cooling configuration, the operational life of the combustor may be increased, the operating efficiency of the combustor may be increased, and/or the operating performance of the combustor may be increased, according to various embodiments.
The combustor liner of this disclosure provides a sacrificial impingement plate to supplement the conventional impingement plate of a conventional double wall design to provide additional dirt filtering for the effusion plate where durability concerns are the most prevalent. Several design parameters such as impingement diameter, dirt injection mass, plate-to-plate spacing, and integration of surface cooling features were evaluated. A design with pin and diamond designs on the middle impingement plate performed the best with 87% reductions in dirt deposition on the effusion plate compared to a similar double wall design. Flow blockage of the cooling holes was also shown to diminish by more than 40% compared to a double wall design with the same amount of dirt injection. Individual pressure drops across each of the layers were used to prove that deposition on the effusion plate was the main driver of flow blockage. As a result, the significant reductions in effusion plate dirt deposition for the disclosed design makes them desirable for improved liner durability.

Discussion of Possible Embodiments

The following are non-exclusive descriptions of possible embodiments of the present invention.
A combustor has a combustor shell defining a plurality of first impingement holes, a particle collection panel defining a plurality of second impingement holes and disposed inward of the combustor shell, and a combustor panel defining a plurality of effusion holes and disposed inward of the particle collection panel. The particle collection panel includes a plurality of raised cooling features disposed on an outward surface of the particle collection panel. The plurality of raised cooling features are configured to promote heat transfer and to collect and/or entrap particulate matter from cooling air flowing through the combustor when the combustor is in operation and each of the plurality of raised cooling features extends outward from an outward surface of the particle collection panel.
The combustor of the preceding paragraph can optionally include, additionally and/or alternatively, any one or more of the following features, configurations and/or additional elements:
A further embodiment of the foregoing combustor, wherein the effusion holes extend from a cold side cooling surface of the combustor panel to a hot side combustion facing surface of the combustor panel, wherein the hot side combustion facing surface is opposite the cold side cooling surface.
A further embodiment of the foregoing combustor, wherein the effusion holes are oriented to create an air film over a hot side of the combustor panel, wherein the effusion holes are configured to protect the combustor panel from hot combustion gases in the combustor chamber.
A further embodiment of the foregoing combustor, wherein the particle collection panel is disposed in an annular cooling cavity between the combustor shell and the combustor panel, such the particle collection panel is disposed inward of the combustor shell and the combustor panel is disposed inward of the particle collection panel.
A further embodiment of the foregoing combustor, wherein the plurality of raised cooling features are pins.
A further embodiment of the foregoing combustor, wherein each of plurality of pins have a cylindrical, ellipsoidal, or structure.
A further embodiment of the foregoing combustor, wherein the plurality of raised cooling features are diamond fins.
A further embodiment of the foregoing combustor, wherein each of the diamond fins include a raised structure having polygonal shape.
A further embodiment of the foregoing combustor, wherein the plurality of raised cooling features are fence fins.
A further embodiment of the foregoing combustor, wherein each of the raised fences is a fence-like structure including an elongated rectangular prism.
A gas turbine engine includes a combustor having a combustor shell defining a plurality of first impingement holes, a particle collection panel defining a plurality of second impingement holes and disposed inward of the combustor shell, and a combustor panel defining a plurality of effusion holes and disposed inward of the particle collection panel. The particle collection panel includes a plurality of raised cooling features disposed on an outward surface of the particle collection panel. The plurality of raised cooling features are configured to promote heat transfer and to collect and/or entrap particulate matter from cooling air flowing through the combustor when the combustor is in operation and each of the plurality of raised cooling features extends outward from an outward surface of the particle collection panel.
The gas turbine engine of the preceding paragraph can optionally include, additionally and/or alternatively, any one or more of the following features, configurations and/or additional elements:
A further embodiment of the foregoing gas turbine engine, wherein the effusion holes extend from a cold side cooling surface of the combustor panel to a hot side combustion facing surface of the combustor panel, wherein the hot side combustion facing surface is opposite the cold side cooling surface.
A further embodiment of the foregoing gas turbine engine, wherein the effusion holes are oriented to create an air film over a hot side of the combustor panel, wherein the effusion holes are configured to protect the combustor panel from hot combustion gases in the combustor chamber.
A further embodiment of the foregoing gas turbine engine, wherein the particle collection panel is disposed in an annular cooling cavity between the combustor shell and the combustor panel, such the particle collection panel is disposed inward of the combustor shell and the combustor panel is disposed inward of the particle collection panel.
A further embodiment of the foregoing gas turbine engine, wherein the plurality of raised cooling features are pins.
A further embodiment of the foregoing gas turbine engine, wherein each of plurality of pins have a cylindrical, ellipsoidal, or structure.
A further embodiment of the foregoing gas turbine engine, wherein the plurality of raised cooling features are diamond fins.
A further embodiment of the foregoing gas turbine engine, wherein each of the diamond fins include a raised structure having polygonal shape.
A further embodiment of the foregoing gas turbine engine, wherein the plurality of raised cooling features are fence fins.
A further embodiment of the foregoing gas turbine engine, wherein each of the raised fences is a fence-like structure including an elongated rectangular prism.
While the invention has been described with reference to an exemplary embodiment(s), it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted for elements thereof without departing from the scope of the invention. In addition, many modifications may be made to adapt a particular situation or material to the teachings of the invention without departing from the essential scope thereof. Therefore, it is intended that the invention not be limited to the particular embodiment(s) disclosed, but that the invention will include all embodiments falling within the scope of the appended claims.

Claims

A combustor comprising:
a combustor shell defining a plurality of first impingement holes;

a particle collection panel defining a plurality of second impingement holes and comprising a plurality of raised cooling features disposed on an outward surface of the particle collection panel, wherein the particle collection panel is disposed inward of the combustor shell; and

a combustor panel defining a plurality of effusion holes, wherein the combustor panel is disposed inward of the particle collection panel;

wherein the plurality of raised cooling features are configured to promote heat transfer and to collect and/or entrap particulate matter from cooling air flowing through the combustor when the combustor is in operation and each of the plurality of raised cooling features extends outward from an outward surface of the particle collection panel.
The combustor of claim 1, wherein the effusion holes extend from a cold side cooling surface of the combustor panel to a hot side combustion facing surface of the combustor panel, wherein the hot side combustion facing surface is opposite the cold side cooling surface.
The combustor of claim 1, wherein the effusion holes are oriented to create an air film over a hot side of the combustor panel, wherein the effusion holes are configured to protect the combustor panel from hot combustion gases in the combustor chamber.
The combustor of any of claims 1 to 3, wherein the particle collection panel is disposed in an annular cooling cavity between the combustor shell and the combustor panel, such the particle collection panel is disposed inward of the combustor shell and the combustor panel is disposed inward of the particle collection panel.
The combustor of any of claims 1 to 4, wherein the plurality of raised cooling features are pins.
The combustor of claim 5, wherein each of plurality of pins have a cylindrical, ellipsoidal, or structure.
The combustor of any of claims 1 to -4, wherein the plurality of raised cooling features are diamond fins.
The combustor of claim 7, wherein each of the diamond fins include a raised structure having polygonal shape.
The combustor of any of claims 1 to 4, wherein the plurality of raised cooling features are fence fins.
The combustor of claim 9, wherein each of the raised fences is a fence-like structure including an elongated rectangular prism.
A gas turbine engine comprising:
the combustor of any of claims 1 to 10.