Gas turbine engine with turbine bucket carrier cooling flowpath

Abstract

A gas turbine engine includes: an outer casing; the inner shell is surrounded by the outer shell, and a shell cavity is defined between the inner shell and the outer shell. A blower is disposed outside the outer housing and is operable to blow in a cooling flow. A turbine bucket carrier is disposed inside the inner housing. The turbine bucket carrier cooling flow path is arranged to direct a cooling flow in contact with the turbine bucket carrier.

Description

Background Art

[0001] A gas turbine engine generally includes a compressor section, a turbine section, and a combustion section disposed between the compressor section and the turbine section. The compressor section includes multiple stages of rotating compressor blades and fixed compressor vanes. The combustion section generally includes multiple combustion chambers. The turbine section includes multiple stages of rotating turbine blades and fixed turbine vanes. The turbine blades and turbine vanes generally operate in a high temperature environment and are internally cooled. Summary of the invention

[0002] In one aspect, a gas turbine engine includes: an outer casing; an inner casing surrounded by the outer casing, a casing cavity being defined between the inner casing and the outer casing; a blower disposed outside the outer casing and operable to blow in a cooling flow; a turbine blade carrier disposed inside the inner casing; and a turbine blade carrier cooling flow path arranged to guide the cooling flow into contact with the turbine blade carrier.

[0003] In one aspect, a gas turbine engine includes: an outer casing; an inner casing surrounded by the outer casing, a casing cavity being defined between the inner casing and the outer casing; a blower disposed outside the outer casing and operable to blow in a cooling flow; a first cooling flow pipe flow-connected to the blower to receive the cooling flow and arranged to guide the cooling flow into the casing cavity; a turbine blade carrier disposed inside the inner casing; and a turbine blade carrier cooling flow path having cooling holes disposed on the inner casing to guide the cooling flow from the casing cavity to contact the turbine blade carrier.

[0004] In one aspect, a gas turbine engine includes: an outer casing; an inner casing surrounded by the outer casing, a casing cavity being defined between the inner casing and the outer casing; a blower disposed outside the outer casing and operable to blow in a cooling flow; a turbine blade carrier disposed inside the outer casing; and a turbine blade carrier cooling flow path having a second cooling flow pipe that is fluidly connected to the blower to receive the cooling flow and is arranged to guide the cooling flow into contact with the turbine blade carrier. BRIEF DESCRIPTION OF THE DRAWINGS

[0005] To easily identify the discussion of any particular element or act, the highest digit(s) in a reference number refers to the figure number in which the element is first introduced.

[0006] Figure 1 is a longitudinal cross-sectional view of a gas turbine engine taken along a plane containing the longitudinal axis or central axis.

[0007] Figure 2 yes Figure 1 A cross-sectional view of a portion of a gas turbine engine is shown to better illustrate a turbine section having turbine bucket carrier cooling flow paths.

[0008] Figure 3 yes Figure 1 A cross-sectional view of a portion of a gas turbine engine is shown to better illustrate a turbine section having another turbine bucket carrier cooling flow path. DETAILED DESCRIPTION

[0009] Before describing in detail any embodiment of the present invention, it should be understood that the present invention is not limited in its application to the details of the structure and arrangement of the components set forth in this description or shown in the following drawings. The present invention can have other embodiments and can be practiced or performed in various ways. In addition, it should be understood that the words and terms used herein are for descriptive purposes and should not be regarded as limiting.

[0010] Various techniques for systems and methods will now be described with reference to the accompanying drawings, wherein similar reference numerals represent similar elements throughout. The drawings discussed below in this patent document and the various embodiments for describing the principles of the present disclosure are intended to be illustrative only and should not be construed in any way to limit the scope of the present disclosure. It will be appreciated by those skilled in the art that the principles of the present disclosure may be implemented with any suitably arranged device. It should be understood that the functions described as being performed by certain system elements may be performed by multiple elements. Similarly, for example, an element may be configured to perform the functions described as being performed by multiple elements. Many innovative teachings of the present application will be described with reference to exemplary non-limiting embodiments.

[0011] In addition, it should be understood that, unless explicitly limited in some examples, the words or phrases used in this article should be interpreted broadly. For example, the terms "include", "have" and "include" and their derivatives mean to include but not limit. Unless the context clearly indicates otherwise, the singular forms "one", "a kind of" and "the" are also intended to include plural forms. In addition, the term "and / or" used in this article refers to and covers any combination and all possible combinations of one or more of the associated listed items in the associated listed items. Unless the context clearly indicates otherwise, the term "or" is inclusive, meaning and / or. The phrases "associated with..." and "associated with this" and their derivatives can mean including, included in, interconnected with, including, included in, connected to or connected with, connected to or connected with, able to communicate with, cooperate with, interlaced, juxtaposed, close to, combined with or combined with, have, have the characteristics of, etc. Furthermore, although multiple embodiments or configurations may be described herein, any features, methods, steps, components, etc. described with respect to one embodiment may also be applicable to other embodiments without specific statement to the contrary.

[0012] In addition, although the terms "first", "second", "third" etc. can be used herein to refer to various elements, information, functions or actions, these elements, information, functions or actions should not be limited by these terms. On the contrary, these digital adjectives are used to distinguish different elements, information, functions or actions from each other. For example, without departing from the scope of the present disclosure, the first element, the first information, the first function or the first action can be referred to as the second element, the second information, the second function or the second action, and similarly, the second element, the second information, the second function or the second action can be referred to as the first element, the first information, the first function or the first action.

[0013] Furthermore, in this specification, the term "axial" or "axially" refers to a direction along the longitudinal axis of the gas turbine engine. The term "radial" or "radially" refers to a direction perpendicular to the longitudinal axis of the gas turbine engine. The term "downstream" or "rearward" refers to a direction along the flow direction. The term "upstream" or "ahead" refers to a direction opposite to the flow direction.

[0014] Additionally, unless the context clearly indicates otherwise, the term "adjacent to..." may mean: one element is fairly close to another element but not in contact with the other element, or the element is in contact with another part. Furthermore, unless otherwise clearly indicated, the phrase "based on" is intended to mean "based at least in part on." The term "about" or "approximately" or similar terms are intended to encompass variations in the value of the dimension within normal industrial manufacturing tolerances. If no industry standard is available, a twenty percent variation will fall within the meaning of these terms unless otherwise indicated.

[0015] Figure 1 An example of a gas turbine engine 100 is illustrated, 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, wherein each compressor stage 114 includes a set of fixed compressor blades 116 or adjustable guide vanes and a set of rotating compressor blades 118. The rotor 134 supports the rotating compressor blades 118 to rotate about the central axis 112 during operation. In some configurations, a single integral rotor 134 extends the length of the gas turbine engine 100 and is supported for rotation by bearings at both ends. In other configurations, the rotor 134 is assembled from several separate spools attached to each other, or may include multiple disk segments attached via one bolt or multiple bolts.

[0016] The compressor section 102 is in fluid communication with the 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 illustrated compressor section 102 is an example of one compressor section 102, and other arrangements and designs are possible.

[0017] In the illustrated configuration, the combustion section 104 includes a plurality of individual combustion chambers 120, each of which operates to mix a flow of fuel with compressed air from the compressor section 102 and combust the air-fuel mixture to produce a flow of high temperature, high pressure combustion gases or exhaust gases 122. Of course, many other arrangements of the combustion section 104 are possible.

[0018] The turbine section 106 includes a plurality of turbine stages 124, wherein each turbine stage 124 includes a number of stationary turbine blades 126 and a number of rotating turbine blades 128. The turbine stage 124 is arranged to receive exhaust gas 122 from the combustion section 104 at a turbine inlet 130 and expand the gas to convert heat 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, pump or other device to be driven. As with the compressor section 102, other designs and arrangements of the turbine section 106 are also possible.

[0019] An exhaust section 110 is positioned downstream of the turbine section 106 and is arranged to receive a flow of expanded exhaust gas 122 from a final 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 efficient operation of the turbine section 106. Many variations and design differences are possible in the exhaust section 110. Therefore, the illustrated exhaust section 110 is merely one example of such variations.

[0020] 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 typically microprocessor-based and includes memory devices and data storage devices 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 users to interact with the control system 132 to provide input or adjustments. In the 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 the power output in an efficient manner.

[0021] 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, flow control valve position, generator load, and generator excitation. Of course, other applications may have fewer or more controllable devices. The control system 132 also monitors various parameters to ensure that the gas turbine engine 100 is operating properly. Some of the parameters monitored may include inlet air temperature, compressor outlet temperature and pressure, combustor outlet temperature, fuel flow rate, generator power output, bearing temperature, etc. Many of these measurements are displayed to the user and are recorded for subsequent review if review is required.

[0022] Figure 2 Picture shows Figure 1A cross-sectional view of a portion of the gas turbine engine 100 is shown, which better illustrates the turbine section 106. The gas turbine engine 100 includes an outer casing 202 and an inner casing 204 surrounded by the outer casing 202. A casing cavity 206 is defined between the outer casing 202 and the inner casing 204. The casing cavity 206 has an annular shape and extends to the exhaust section 110. Components of the gas turbine engine 100, such as the stationary turbine buckets 126 and the rotating turbine blades 128, are disposed within the inner casing 204. Figure 2 A portion of one rotating turbine blade 128 of the final stage of turbine section 106 is shown in FIG.

[0023] The turbine blade carrier 214 is disposed within the inner casing 204. The turbine blade carrier 214 carries a plurality of fixed turbine blades 126 ( Figure 2 216). The turbine bucket carrier 214 extends over the plurality of rotating turbine blades 128. The turbine bucket carrier 214 extends over the plurality of rotating turbine blades 128 of the last stage of the turbine section 106 relative to the rear end of the working flow 216. The working flow 216 may include Figure 1 Exhaust gas 122 is shown. Turbine blade tip clearance 218 is defined as the clearance between turbine bucket carrier 214 and rotating turbine blades 128 .

[0024] The blower 208 is disposed outside the outer shell 202. The first cooling flow tube 212 is flow-connected to the blower 208 and passes through the outer shell 202. The blower 208 blows in a cooling flow 210 and delivers the cooling flow 210 to the first cooling flow tube 212. The cooling flow 210 is guided into the shell cavity 206 by the first cooling flow tube 212 and flows to the exhaust portion 110. The first cooling flow tube 212 is one of a plurality of first cooling flow tubes 212 circumferentially distributed around the outer shell 202. The plurality of first cooling flow tubes 212 are flow-connected to the blower 208 through a manifold.

[0025] The cooling flow 210 may include ambient air that is external to the gas turbine engine 100 and has a standard atmospheric temperature and pressure at the geographic location of the gas turbine engine 100. The cooling flow 210 may also include other types of flows, such as flows from the compressor section 102. The blower 208 may be a centrifugal blower 208. Other types of blowers 208 are also possible.

[0026] The turbine bucket carrier cooling flow path 222 is arranged to direct the cooling flow 210 to contact the turbine bucket carrier 214 to cool the turbine bucket carrier 214. Figure 2In the illustrated configuration, the turbine bucket carrier cooling flow path 222 includes a cooling hole 220 passing through the inner casing 204. The cooling hole 220 directs a portion of the cooling flow 210 from the casing cavity 206 to contact the turbine bucket carrier 214, thereby impingement cooling the turbine bucket carrier 214. The cooling hole 220 is one of a plurality of cooling holes 220 distributed circumferentially around the inner casing 204. The plurality of cooling holes 220 form the turbine bucket carrier cooling flow path 222.

[0027] The cooling hole 220 is disposed at one end of the turbine bucket carrier 214. Figure 2 In the illustrated configuration, the cooling holes 220 are disposed at the aft end of the turbine bucket carrier 214 relative to the working flow 216. In other configurations, the cooling holes 220 may be disposed at the forward end of the turbine bucket carrier 214 relative to the working flow 216.

[0028] The filter 224 is fluidly connected to the blower 208. The filter 224 filters the cooling flow 210 before the cooling flow 210 flows into the first cooling flow tube 212. Figure 2 In the illustrated configuration, the filter 224 is disposed upstream of the blower 208 relative to the cooling flow 210, so that the cooling flow 210 is filtered before being blown into the blower 208. In other configurations, the filter 224 may be disposed downstream of the blower 208 relative to the cooling flow 210, so that the cooling flow 210 is filtered after flowing out of the blower 208 and before flowing into the first cooling flow tube 212. The filter 224 may be a centrifugal filter 224. Other types of filters 224 are also possible.

[0029] Figure 3 Picture shows Figure 1 A cross-sectional view of a portion of gas turbine engine 100 is shown to better illustrate turbine section 106. Figure 3 In the illustrated configuration, the turbine blade carrier cooling flow path 222 includes a second cooling flow tube 302 that is flow-connected to the blower 208 and passes through the outer shell 202 and the inner shell 204. The blower 208 blows the cooling flow 210 and delivers the cooling flow 210 to the second cooling flow tube 302. The second cooling flow tube 302 guides the cooling flow 210 to contact the turbine blade carrier 214 to perform impingement cooling on the turbine blade carrier 214. The second cooling flow tube 302 is one of a plurality of second cooling flow tubes 302 that are circumferentially distributed around the outer shell 202 and the inner shell 204. The plurality of second cooling flow tubes 302 are flow-connected to the blower 208 through a manifold. The plurality of second cooling flow tubes 302 form the turbine blade carrier cooling flow path 222.

[0030] The cooling flow 210 may include ambient air that is external to the gas turbine engine 100 and has a standard atmospheric temperature and pressure at the geographic location of the gas turbine engine 100. The cooling flow 210 may also include other types of flows, such as flows from the compressor section 102. The blower 208 may be a centrifugal blower 208. Other types of blowers 208 are also possible.

[0031] The second cooling flow pipe 302 is disposed at one end of the turbine bucket carrier 214. Figure 3 In the illustrated configuration, the second cooling flow tube 302 is disposed at the aft end of the turbine bucket carrier 214 relative to the turbine bucket carrier 214. In other configurations, the second cooling flow tube 302 may be disposed at the forward end of the turbine bucket carrier 214 relative to the working flow 216.

[0032] The turbine bucket carrier cooling flow path 222 includes a flow control valve 304 disposed outside the outer casing 202 and in flow connection with the second cooling flow pipe 302. The flow control valve 304 controls the cooling flow 210 passing through the second cooling flow pipe 302 to contact the turbine bucket carrier 214. The flow control valve 304 is movable between an open position and a closed position to control the cooling flow 210 flowing to the turbine bucket carrier 214. The flow control valve 304 may be an on / off valve.

[0033] exist Figure 3 In the illustrated configuration, the filter 224 is disposed upstream of the blower 208 relative to the cooling flow 210, so that the cooling flow 210 is filtered before being blown into the blower 208. In other configurations, the filter 224 may be disposed downstream of the blower 208 relative to the cooling flow 210, so that the cooling flow 210 is filtered after flowing out of the blower 208 and before flowing into the first cooling flow tube 212. The filter 224 may be a centrifugal filter 224. Other types of filters 224 are also possible.

[0034] Figure 3 The construction is otherwise similar to Figure 2 The structure is no longer referenced Figure 3 Describe it in detail.

[0035] During operation, refer to Figure 2 and Figure 3, the blower 208 blows the cooling flow 210 into the first cooling flow pipe 212. The cooling flow 210 is guided into the casing cavity 206 by the first cooling flow pipe 212, and flows to the exhaust portion 110 to cool the components of the exhaust portion 110. One of the components of the exhaust portion 110 includes an exhaust casing. After cooling the exhaust casing, the cooling flow 210 is guided to cool the rotating turbine blades 128 of the last stage of the turbine section 106, and is used as a purge air for the oil seal of the gas turbine engine 100. The cooling flow 210 from the blower 208 is also guided by the turbine bucket carrier cooling flow path 222 to cool the turbine bucket carrier 214.

[0036] Reference Figure 2 The turbine bucket carrier cooling flow path 222 includes a plurality of cooling holes 220 passing through the inner casing 204. A portion of the cooling flow 210 is directed from the casing cavity 206 by the plurality of cooling holes 220 to contact the turbine bucket carrier 214, thereby cooling the turbine bucket carrier 214.

[0037] Reference Figure 3 , the turbine bucket carrier cooling flow path 222 includes a plurality of second cooling flow tubes 302 that are flow-connected to the blower 208 and pass through the outer casing 202 and the inner casing 204. A portion of the cooling flow 210 from the blower 208 is directed by the plurality of second cooling flow tubes 302 to contact the turbine bucket carrier 214, thereby cooling the turbine bucket carrier 214. The flow control valve 304 moves between an open position and a closed position to control the cooling flow 210 passing through the plurality of second cooling flow tubes 302 to contact the turbine bucket carrier 214 according to the performance requirements of the gas turbine engine 100. For example, the flow control valve 304 may be closed during startup and then opened at a certain point in time after startup to enable the cooling flow 210 to flow to the turbine bucket carrier 214, thereby cooling the turbine bucket carrier 214.

[0038] The turbine bucket carrier cooling flow path 222 utilizes the cooling flow 210 provided by the blower 208 to cool the turbine bucket carrier 214 and also cool the exhaust casing. The cooling flow 210 is supplied from a source external to the gas turbine engine 100. The cooling flow 210 may be ambient air from outside the gas turbine engine 100. This arrangement does not negatively impact the power output of the gas turbine engine 100. The cooling flow 210 from the ambient air has a standard atmospheric temperature and pressure at the geographical location of the gas turbine engine 100, which provides stable cooling for the turbine bucket carrier 214. The cooling flow 210 allows any thermal variations within the turbine bucket carrier 214 to be controlled and reduced, and thus maintains the desired turbine blade tip clearance 218 between the turbine bucket carrier 314 and the rotating turbine blades 128.

[0039] Although the exemplary embodiments of the present disclosure have been described in detail, those skilled in the art will understand that various changes, substitutions, variations, and improvements may be made to what is disclosed herein without departing from the spirit and scope of the disclosure in its broadest form.

[0040] Nothing in this application should be construed as implying that any particular element, step, act, or function is essential to be included in the claims: the scope of patented subject matter is limited only by the allowed claims. Furthermore, unless the exact phrase "means for..." is followed by a participle, none of the claims are intended to invoke a means-plus-function claim construction.

[0041] Reference numerals

[0042] 100: Gas turbine engine

[0043] 102: Compressor section

[0044] 104: Combustion section

[0045] 106: Turbine section

[0046] 108: Entrance section

[0047] 110: Exhaust part

[0048] 112: Central axis

[0049] 114: Compressor stage

[0050] 116: Fixed compressor blades

[0051] 118: Rotary compressor blades

[0052] 120: Combustion Chamber

[0053] 122: Exhaust

[0054] 124: Turbine stage

[0055] 126: Fixed turbine blades

[0056] 128: Rotating turbine blades

[0057] 130: Turbine inlet

[0058] 132: Control System

[0059] 134: Rotor

[0060] 202: Outer shell

[0061] 204: Inner shell

[0062] 206: Shell cavity

[0063] 208: Blower

[0064] 210: Cooling flow

[0065] 212: First cooling flow pipe

[0066] 214: Turbine blade carrier

[0067] 216: Workflow

[0068] 218: Turbine blade tip clearance

[0069] 220: Cooling holes

[0070] 222: Turbine blade carrier cooling flow path

[0071] 224: Filter

[0072] 302: Second cooling flow pipe

[0073] 304: Flow control valve

Claims

1. A gas turbine engine, comprising: outer shell; An inner shell, the inner shell is surrounded by the outer shell, and a shell cavity is defined between the inner shell and the outer shell; a blower disposed outside the outer shell and operable to blow a cooling flow; a turbine blade carrier, the turbine blade carrier being disposed inside the inner casing; as well as A turbine bucket carrier cooling flow path is arranged to direct the cooling flow into contact with the turbine bucket carrier. 2 . The gas turbine engine according to claim 1 , further comprising a first cooling flow duct, the first cooling flow duct being flow-connected to the blower to receive the cooling flow and arranged to guide the cooling flow into the casing cavity.

3. The gas turbine engine according to claim 2, wherein: The turbine bucket carrier cooling flow path includes cooling holes arranged on the inner casing to direct the cooling flow from the casing cavity to contact the turbine bucket carrier.

4. The gas turbine engine according to claim 3, wherein: The cooling holes are positioned at a rear end of the turbine bucket carrier relative to a working flow.

5. The gas turbine engine according to claim 3, wherein: The cooling hole is one of a plurality of cooling holes distributed circumferentially around the inner casing.

6. The gas turbine engine according to claim 1, wherein: The turbine bucket carrier cooling flow path includes a second cooling flow tube that is fluidly connected to the blower to receive the cooling flow and is arranged to direct the cooling flow into contact with the turbine bucket carrier.

7. The gas turbine engine according to claim 6, wherein: The turbine bucket carrier cooling flow path includes a flow control valve in flow connection with the second cooling flow tube, and wherein the flow control valve is movable between an open position and a closed position to control the cooling flow through the second cooling flow tube in contact with the turbine bucket carrier.

8. The gas turbine engine according to claim 6, wherein: The second cooling flow duct is positioned at a rear end of the turbine bucket carrier relative to a working flow.

9. The gas turbine engine according to claim 6, wherein: The second cooling flow tube is one of a plurality of second cooling flow tubes distributed circumferentially around the outer shell and the inner shell.

10. The gas turbine engine of claim 1, further comprising a filter in fluid connection with the blower.

11. The gas turbine engine according to claim 1, wherein: The cooling flow includes ambient air external to the gas turbine engine.

12. A gas turbine engine comprising: outer shell; An inner shell, the inner shell is surrounded by the outer shell, and a shell cavity is defined between the inner shell and the outer shell; a blower disposed outside the outer shell and operable to blow a cooling flow; a first cooling flow conduit, the first cooling flow conduit being in flow connection with the blower to receive the cooling flow and arranged to direct the cooling flow into the housing cavity; a turbine blade carrier, the turbine blade carrier being disposed inside the inner casing; as well as A turbine bucket carrier cooling flow path includes cooling holes arranged on the inner casing to direct the cooling flow from the casing cavity to contact the turbine bucket carrier.

13. The gas turbine engine according to claim 12, wherein: The cooling holes are positioned at a rear end of the turbine bucket carrier relative to a working flow.

14. The gas turbine engine according to claim 12, wherein: The cooling hole is one of a plurality of cooling holes distributed circumferentially around the inner casing.

15. The gas turbine engine of claim 12, further comprising a filter in fluid connection with the blower.

16. A gas turbine engine comprising: outer shell; An inner shell, the inner shell is surrounded by the outer shell, and a shell cavity is defined between the inner shell and the outer shell; a blower disposed outside the outer shell and operable to blow a cooling flow; A turbine blade carrier, the turbine blade carrier being arranged inside the outer shell; as well as A turbine bucket carrier cooling flow path includes a second cooling flow tube in flow connection with the blower to receive the cooling flow and arranged to guide the cooling flow into contact with the turbine bucket carrier.

17. The gas turbine engine according to claim 16, wherein: The turbine bucket carrier cooling flow path includes a flow control valve in flow connection with the second cooling flow tube, and wherein the flow control valve is movable between an open position and a closed position to control the cooling flow through the second cooling flow tube in contact with the turbine bucket carrier.

18. The gas turbine engine according to claim 16, wherein: The second cooling flow duct is positioned at a rear end of the turbine bucket carrier relative to a working flow.

19. The gas turbine engine according to claim 16, wherein: The second cooling flow tube is one of a plurality of second cooling flow tubes distributed circumferentially around the outer shell and the inner shell.

20. The gas turbine engine of claim 16, further comprising a filter in fluid connection with the blower.

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