Gas turbine engine rotor heat shroud
By using a heat shield in the gas turbine engine rotor to separate the cooling flow path and the conical space, the problem of failure of the support cone in high temperature environments is solved, and the mechanical stability and life of the rotor are improved.
Patent Information
- Application Number
- CN202411966540.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Priority Date
- 2024-01-26
- Filing Date
- 2024-12-30
- Publication Date
- 2025-07-29
AI Technical Summary
In gas turbine engines, the support cone does not support the center-tight bolts, which may fail in high temperature environments, affecting the stability and life of the rotor.
A rotor structure is designed in which the first side of the support cone in contact with the center-tied bolt is separated into a cooling flow path and a conical space by a heat shield which is arranged adjacent to the support cone to protect the support cone from being heated quickly and maintain proper contact between the support cone and the center-tied bolt.
Effectively protect the support cone from being heated quickly, ensure stable contact between the support cone and the center tightening bolt, and improve the mechanical stability and life of the rotor.
Smart Images
Figure CN120384789A_ABST
Abstract
Description
BACKGROUND OF THE INVENTION
[0001] A gas turbine engine generally includes a compressor section, a turbine section, and a combustion section disposed therebetween. The compressor section typically includes multiple stages of rotating compressor blades and stationary compressor vanes to produce compressed air. The combustion section typically includes multiple burners to produce a hot working fluid by burning a mixture of compressed air and fuel. The turbine section typically includes multiple stages of rotating turbine blades and stationary turbine vanes to expand the hot working fluid and convert the fluid energy into mechanical energy. The rotating turbine blades and the stationary turbine vanes typically operate in a high temperature environment and are internally cooled.
[0002] A gas turbine engine generally includes a rotor that rotates the rotating compressor blades and the rotating turbine blades. The rotor may include a central tie bolt and a support cone that supports the central tie bolt. During operation of the gas turbine engine, sufficient support of the central tie bolt by the support cone needs to be maintained. SUMMARY OF THE INVENTION
[0003] In one aspect, a rotor is provided. The rotor includes a rotor disk, a rear shaft disposed downstream of the rotor disk, a central tie bolt extending along a central axis and connecting the rotor disk and the rear shaft in a direction parallel to the central axis, the central tie bolt being surrounded by the rotor disk and the rear shaft, a space being formed between the central tie bolt, the rotor disk, and the rear shaft, a support cone disposed in the space to support the central tie bolt, a first side of the support cone being in contact with the central tie bolt, and a thermal shroud disposed adjacent to the support cone to divide the space into a cooling flow path that allows a cooling flow to pass through and a conical space that the cooling flow does not pass through, the support cone being disposed in the conical space. BRIEF DESCRIPTION OF THE DRAWINGS
[0004] To readily identify the discussion of any particular element or act, one or more of the most significant digits in the reference numerals refer to the reference numeral that first introduced the element.
[0005] Figure 1 is a longitudinal cross-sectional view of a gas turbine engine taken along a plane including a longitudinal axis or a central axis.
[0006] Figure 2 is Figure 1 a cross-sectional view of a first portion of the gas turbine engine.
[0007] Figure 3 is Figure 1 a cross-sectional view of a second portion of the gas turbine engine. DETAILED DESCRIPTION
[0008] Before explaining any embodiments of the present invention in detail, it should be understood that the application of the present invention is not limited to the details of the construction and arrangement of components set forth in this specification or shown in the following drawings. The present invention is capable of other embodiments and of being practiced or carried out in various ways. Further, it should be understood that the language and terminology used herein are for the purpose of description and should not be regarded as limiting.
[0009] Various techniques related to systems and methods will now be described with reference to the drawings, where like reference numerals always denote like elements. The following discussion of the drawings and the various embodiments used to describe the principles of the present invention in this patent document are for illustrative purposes only and should not be construed in any way as limiting the scope of the present invention. Those skilled in the art will understand that the principles of the present invention can be implemented in any suitably arranged device. It should be understood that functions described as being performed by certain system elements may be performed by multiple elements. Similarly, for example, one element may be configured to perform functions described as being performed by multiple elements. Many innovative teachings of this application will be described with reference to exemplary non-limiting embodiments.
[0010] It should be understood that words or phrases used in the present invention should be construed broadly unless explicitly limited in some examples. For example, the terms "comprising," "having," and "including" and their derivatives mean including without limitation. The singular forms "a," "an," and "the" are also intended to include the plural forms unless the context clearly indicates otherwise. Additionally, the term "and / or" as used in the present invention refers to and encompasses any and all possible combinations of one or more of the associated listed items. The term "or" is inclusive and means and / or unless the context clearly indicates otherwise. The phrases "associated with" and "associated therewith" and their derivatives may mean including, being included within, interconnected with, containing, being contained within, connected to or coupled with, communicating with, collaborating with, interlacing, juxtaposing, approaching, bound to or coupled with, having, having the characteristics of, etc. Further, while the present invention describes multiple embodiments or configurations, any feature, method, step, component, etc. described with respect to one embodiment equally applies to other embodiments in the absence of a contrary specific statement.
[0011] Although the terms "first," "second," "third," etc. may be used in the present invention to refer to various elements, information, functions, or actions, these elements, information, functions, or actions should not be limited by these terms. Instead, these numerical adjectives are used to distinguish between different elements, information, functions, or actions. For example, a first element, information, function, or action may be referred to as a second element, information, function, or action, and similarly, a second element, information, function, or action may be referred to as a first element, information, function, or action without departing from the scope of the present invention.
[0012] In the specification, the term "axial" or "axially" refers to the direction along the longitudinal axis of the gas turbine engine. The term "radial" or "radially" refers to the direction perpendicular to the longitudinal axis of the gas turbine engine. The term "downstream" or "rearward" refers to the direction along the flow direction. The term "upstream" or "forward" refers to the direction opposite to the flow direction.
[0013] In addition, the term "adjacent" may mean that an element is relatively close to but not in contact with another element, or that the element is in contact with another part, unless the context clearly indicates otherwise. In addition, the phrase "based on" is intended to mean "at least partially based on", unless clearly stated otherwise. The term "about" or "substantially" or similar terms are intended to cover variations in values within the normal industrial manufacturing tolerances for that dimension. If there is no available industrial standard, a 20% variation will fall within the meaning of these terms, unless otherwise stated.
[0014] Figure 1 An example of a gas turbine engine 100 is shown, which includes a compressor section 102, a combustion section 104, and a turbine section 106 arranged along a central axis 112. The compressor section 102 includes a plurality of compressor stages 114, each compressor stage 114 including a set of stationary compressor blades 116 or adjustable guide vanes and a set of rotating compressor rotor blades 118. A rotor 134 supports the rotating compressor rotor blades 118 for rotation about the central axis 112 during operation. In some configurations, a single one-piece rotor 134 extends the length of the gas turbine engine 100 and is supported at either end by bearings for rotation. In other configurations, the rotor 134 is assembled from several separate main shafts attached to each other, or may include a plurality of disk segments attached by one or more bolts.
[0015] The compressor section 102 is in fluid communication with an inlet section 108 to allow the gas turbine engine 100 to draw atmospheric air into the compressor section 102. During operation of the gas turbine engine 100, the compressor section 102 draws in atmospheric air and compresses the air for delivery to the combustion section 104. The compressor section 102 shown is an example of one compressor section 102, and other arrangements and designs are possible.
[0016] In the illustrated configuration, the combustion section 104 includes a plurality of separate burners 120, each burner operating to mix a fuel stream with compressed air from the compressor section 102 and combust the air-fuel mixture to produce a stream of high-temperature, high-pressure combusted gas or exhaust 122. Of course, many other arrangements of the combustion section 104 are possible.
[0017] The turbine section 106 includes a plurality of turbine stages 124, each turbine stage 124 including a plurality of stationary turbine blades 126 and a plurality of rotating turbine vanes 128. The turbine stages 124 are arranged to receive the exhaust gas 122 from the combustion section 104 at the turbine inlet 130 and expand the gas to convert thermal energy and pressure energy into rotational or mechanical work. The turbine section 106 is connected to the compressor section 102 to drive the compressor section 102. For a gas turbine engine 100 used for power generation or as a prime mover, the turbine section 106 is also connected to a generator, a pump, or other device to be driven. As with the compressor section 102, other designs and arrangements of the turbine section 106 are possible.
[0018] The exhaust section 110 is located downstream of the turbine section 106 and is arranged to receive the expanded flow of the exhaust gas 122 from the last turbine stage 124 in the turbine section 106. The exhaust section 110 is arranged to effectively direct the exhaust gas 122 away from the turbine section 106 to ensure the effective operation of the turbine section 106. The exhaust section 110 can have many variations and design differences. Thus, the illustrated exhaust section 110 is only one example of these variations.
[0019] The control system 132 is coupled to the gas turbine engine 100 and operates to monitor various operating parameters and control various operations of the gas turbine engine 100. In a preferred configuration, the control system 132 is generally microprocessor-based and includes a memory device and a data storage device for collecting, analyzing, and storing data. In addition, the control system 132 provides output data to various devices, including monitors, printers, indicators, etc., which allow a user to interact with the control system 132 to provide input or make adjustments. In an example of a power generation system, a user can input a power output set point, and the control system 132 can adjust various control inputs to achieve that power output in an efficient manner.
[0020] The control system 132 can control various operating parameters, including but not limited to variable inlet guide vane position, fuel flow rate and pressure, engine speed, valve position, generator load, and generator excitation. Of course, other applications can have fewer or more controllable devices. The control system 132 also monitors various parameters to ensure the normal operation of the gas turbine engine 100. Some of the parameters monitored can include inlet air temperature, compressor outlet temperature and pressure, burner outlet temperature, fuel flow rate, generator power output, bearing temperature, etc. Many of these measurements are displayed to the user and are recorded for later inspection (if such inspection is necessary).
[0021] The rotor 134 includes a plurality of rotor disks 136, a front shaft 138 disposed at the front end of the rotor 134, and a rear shaft 140 disposed at the rear end of the rotor 134. The rear shaft 140 is disposed downstream of the last rotor disk 136, and the last rotor disk 136 supports the last rotating turbine blade 128 of the last turbine stage 124.
[0022] The central fastening bolt 142 extends along the central axis 112 and connects the plurality of rotor disks 136, the front shaft 138, and the rear shaft 140 in a direction parallel to the central axis 112. The central fastening bolt 142 is surrounded by the plurality of rotor disks 136, the front shaft 138, and the rear shaft 140 around the central axis 112. A plurality of support cones 144 are disposed in a direction parallel to the central axis 112 to support the central fastening bolt 142 and tune the natural frequency of the central fastening bolt 142. A space 146 is formed between the central fastening bolt 142, the plurality of rotor disks 136, and the rear shaft 140.
[0023] Figure 2 is Figure 1 a cross-sectional view of a first portion 200 of the gas turbine engine 100. The first portion 200 may be in an intermediate section between the compressor section 102 and the turbine section 106.
[0024] The support cone 144 is disposed between an upstream rotor disk 136 and a downstream rotor disk 136 that are directly adjacent to each other. The support cone 144 has a generally Z-shaped configuration, which has a first side 202 and a second side 204. The first side 202 contacts the central fastening bolt 142. The second side 204 is inserted into a first annular groove 206 defined on the downstream side of the upstream rotor disk 136. The first side 202 is in close contact with the central fastening bolt 142, for example, by shrink fitting. The second side 204 is in loose contact with the upstream rotor disk 136.
[0025] The thermal shroud 208 is disposed upstream adjacent to the support cone 144. The thermal shroud 208 has a first plate 210 and a second plate 212 that form a T-shaped cross-section. The first plate 210 and the second plate 212 are cylindrical plates around the central axis 112. The first plate 210 extends parallel to the central axis 112. A first end 214 of the first plate 210 is disposed radially outside the support cone 144. A second end 216 of the first plate 210 is disposed radially below the downstream rotor disk 136. The second plate 212 is connected to the first plate 210 and extends between the central fastening bolt 142 and the first plate 210. The second plate 212 is in close contact with the central fastening bolt 142, for example, by shrink fitting.
[0026] The support cone 144 and the heat shield 208 are disposed within the space 146. The heat shield 208 divides the space 146 into a cooling flow path 218 and a conical space 220. The cooling flow path 218 permits the cooling flow 222 to pass therethrough and directs the cooling flow 222 towards the turbine section 106. The conical space 220 does not pass the cooling flow 222. The support cone 144 is disposed within the conical space 220.
[0027] Figure 3 is Figure 1 A cross-sectional view of a second portion 300 of a gas turbine engine. The second portion 300 may be in a rear section including the last turbine stage 124 and the exhaust section 110.
[0028] The support cone 144 is disposed between the rotor disk 136 and the rear shaft 140. A first side 202 of the support cone 144 contacts the central tie bolt 142. A second side 204 of the support cone 144 is inserted into a second annular groove 302 defined on the upstream side of the rear shaft 140. The first side 202 is in tight contact with the central tie bolt 142, for example, by an interference fit. The second side 204 is in loose contact with the rear shaft 140.
[0029] The heat shield 304 is disposed adjacent to the support cone 144 upstream thereof. The heat shield 304 has a first plate 306 and a second plate 308 that form an L-shaped cross-section. The first plate 306 and the second plate 308 are cylindrical plates about the central axis 112. The first plate 306 extends parallel to the central axis 112 through a gap 310 defined between the rotor disk 136 and the rear shaft 140. A first end 312 of the first plate 306 is inserted into a third annular groove 316 defined on the downstream side of the rotor disk 136. The first end 312 is in loose contact with the rotor disk 136. A second end 314 of the first plate 306 is connected to the second plate 308. The second plate 308 extends between the central tie bolt 142 and the first plate 306. The second plate 308 is in tight contact with the central tie bolt 142, for example, by an interference fit. A metering hole 318 is defined through a section of the first plate 306 within the gap 310 to allow the cooling flow 222 to leave the rotor disk 136 from the cooling flow path 218.
[0030] The support cone 144 and the heat shield 304 are disposed within the space 146. The heat shield 304 divides the space 146 into a cooling flow path 218 and a conical space 220. The cooling flow path 218 permits the cooling flow 222 to pass therethrough and directs the cooling flow 222 to the turbine section 106. The conical space 220 does not pass the cooling flow 222. The support cone 144 is disposed within the conical space 220.
[0031] In operation, the support cone 144 expands radially due to centrifugal force and thermal expansion. Accordingly, the second side 204 of the support cone 144 moves radially outward within the first annular groove 206 in the first portion 200 and within the second annular groove 302 in the second portion 300. The support cone 144 bends due to the radially outward movement. Thereby, the central tie bolt 142 is supported by the support cone 144.
[0032] The cooling flow 222 is drawn from the compressor section 102 and directed through the rotor disk 136 into the cooling flow path 218. The cooling flow 222 flows through the cooling flow path 218 to the turbine section 106 to cool the rotor 134. The cooling flow 222 is directed out of the rotor disk 136 through the flow restrictor orifice 318.
[0033] The thermal shields 208 and 304 protect the support cone 144 from being rapidly heated and separate the support cone 144 from the cooling flow 222. Thus, proper contact is maintained between the support cone 144 and the central tie bolt 142 such that the central tie bolt 142 is adequately supported by the support cone 144.
[0034] As Figure 2 shown, in the first portion 200 which may be in the intermediate section, the thermal shield 208 also axially holds the support cone 144 deep within the rotor disk 136. As Figure 3 shown, in the second portion 300 which may be in the rear section, the thermal shield 304 also includes a flow restrictor orifice 318 to direct the cooling flow 222 out of the rotor disk 136. The flow restrictor orifice 318 can be easily machined in the thermal shield 304.
[0035] Although the exemplary embodiments of the present invention have been described in detail, those skilled in the art will understand that various changes, substitutions, variations, and improvements of the present disclosure can be made without departing from the spirit and scope of the broadest form of the present invention.
[0036] None of the descriptions in this application should be construed as implying that any particular element, step, act, or function is an essential element that must be included within the scope of the claims: the scope of the patent subject matter is defined only by the allowed claims. Further, these claims are not intended to invoke the apparatus - plus - function claim construction unless the recitation is followed by the exact words "means for".
[0037] 100 Gas turbine engine
[0038] 102 Compressor section
[0039] 104 Combustion section
[0040] 106 Turbine section
[0041] 108 Inlet section
[0042] 110 Exhaust section
[0043] 112 Central axis
[0044] 114 Compressor stage
[0045] 116 Fixed compressor vane
[0046] 118 Rotating compressor blade
[0047] 120 Burner
[0048] 122 Exhaust
[0049] 124 Turbine stage
[0050] 126 Fixed turbine vane
[0051] 128 Rotating turbine blade
[0052] 130 Turbine inlet
[0053] 132 Control system
[0054] 134 Rotor
[0055] 136 Rotor disc
[0056] 138 Front axle
[0057] 140 Rear axle
[0058] 142 Central fastening bolt
[0059] 144 Support cone
[0060] 146 Space
[0061] 200 First part
[0062] 202 First side
[0063] 204 Second side
[0064] 206 First annular groove
[0065] 208 Thermal cover
[0066] 210 First plate
[0067] 212 Second plate
[0068] 214 First end
[0069] 216 Second end
[0070] 218 Cooling flow path
[0071] 220 Conical space
[0072] 222 Cooling flow
[0073] 300 Second part
[0074] 302 Second annular groove
[0075] 304 Thermal cover
[0076] 306 First plate
[0077] 308 Second plate
[0078] 310 Gap
[0079] 312 First end
[0080] 314 Second end
[0081] 316 Third annular groove
[0082] 318 Restriction orifice.
Claims
1. A rotor (134), comprising: A rotor disk (136); A rear shaft (140), the rear shaft (140) being arranged downstream of the rotor disk (136); A central fastening bolt (142), the central fastening bolt (142) extending along a central axis (112) and connecting the rotor disk (136) and the rear shaft (140) in a direction parallel to the central axis (112), the central fastening bolt (142) being surrounded by the rotor disk (136) and the rear shaft (140); A space (146), the space (146) being formed between the central fastening bolt (142), the rotor disk (136) and the rear shaft (140); A support cone (144), the support cone (144) being disposed within the space (146) and supporting the central fastening bolt (142), a first side (202) of the support cone (144) contacting the central fastening bolt (142); and A thermal shroud (208), the thermal shroud (208) being disposed adjacent to the support cone (144) so as to divide the space (146) into a cooling flow path (218) allowing a cooling flow (222) to pass through and a conical space (220) through which the cooling flow (222) does not pass, the support cone (144) being disposed within the conical space (220).
2. The rotor (134) according to claim 1, further comprising a downstream rotor disk (136), the downstream rotor disk (136) being connected to the central fastening bolt (142) and being arranged directly adjacent to a downstream side of the rotor disk (136), wherein the support cone (144) is disposed between the rotor disk (136) and the downstream rotor disk (136).
3. The rotor (134) according to claim 2, wherein, A first annular groove (206) is defined on the downstream side of the rotor disk (136), and wherein a second side (204) of the support cone (144) is inserted into the first annular groove (206).
4. The rotor (134) according to claim 2, wherein, The thermal shroud (208) is disposed downstream of the support cone (144).
5. The rotor (134) according to claim 2, wherein, The thermal shroud (208) includes a first plate (210) and a second plate (212) forming a T-shaped cross-section, and wherein the first plate (210) and the second plate (212) are cylindrical plates around the central axis (112).
6. The rotor (134) according to claim 5, wherein, The first plate (210) extends parallel to the central axis (112), wherein a first end (214) of the first plate (210) is disposed radially outside the support cone (144), and wherein a second end (216) of the first plate (210) is disposed radially below the downstream rotor disk (136).
7. The rotor (134) according to claim 6, wherein, The second plate (212) is connected to the first plate (210) and extends between the central fastening bolt (142) and the first plate (210).
8. The rotor (134) according to claim 1, wherein, The rotor disk (136) is arranged to be directly adjacent to the upstream side of the rear shaft (140), and wherein the support cone (144) is arranged between the rotor disk (136) and the rear shaft (140).
9. The rotor (134) according to claim 8, wherein, A second annular groove (302) is defined on the upstream side of the rear shaft (140), and wherein the second side (204) of the support cone (144) is inserted into the second annular groove (302).
10. The rotor (134) according to claim 8, wherein, The heat shield (208) is provided upstream of the support cone (144).
11. The rotor (134) according to claim 8, wherein, The heat shield (208) includes a first plate (306) and a second plate (308) forming an L-shaped cross-section, wherein the first plate (306) and the second plate (308) are cylindrical plates around the central axis (112).
12. The rotor (134) according to claim 11, wherein, A third annular groove (316) is defined on the downstream side of the rotor disk (136), and wherein the first end (312) of the first plate (306) is inserted into the third annular groove (316), and wherein the second end (314) of the first plate (306) is connected to the second plate (308).
13. The rotor (134) according to claim 11, wherein, A gap (310) is defined between the rotor disk (136) and the rear shaft (140), and wherein the first plate (306) extends parallel to the central axis (112) and passes through the gap (310).
14. The rotor (134) according to claim 13, wherein, The second plate (308) is connected to the first plate (306) and extends between the central tie bolt (142) and the first plate (306).
15. The rotor (134) according to claim 13, wherein, A flow-limiting hole (318) is defined in the section of the first plate (306) located within the gap (310).