Patent Application
20230313697
An industrial gas turbine engine typically includes a compressor section, a turbine section, and a combustion section disposed therebetween. The compressor section includes multiple stages of rotating compressor blades and stationary compressor vanes. The combustion section typically includes a plurality of combustors.
The turbine section includes multiple stages of rotating turbine blades and stationary turbine vanes. Turbine blades and vanes often operate in a high temperature environment and are internally cooled.
A guide vane in a gas turbine engine includes: an inner platform; an outer platform; a first vane airfoil extending between the inner platform and the outer platform; and a second vane airfoil extending between the inner platform and the outer platform and spaced apart from the first guide vane in the circumferential direction.
A guide vane in a gas turbine engine includes: an inner platform; an outer platform including a front hook and a rear hook; a vane airfoil extending between the inner platform and the outer platform; a front locking feature disposed on the front hook; and a rear locking feature disposed on the rear hook.
A guide vane in a gas turbine engine includes: an inner platform; an outer platform; and a vane airfoil extending between the inner platform and the outer platform, the vane airfoil including a pressure sidewall and a suction sidewall, an upstream end of the pressure sidewall and an upstream end of the suction sidewall meeting at a leading edge, a downstream end of the suction sidewall extending downstream further from a downstream end of the pressure sidewall, the downstream end of the suction sidewall forming a trailing edge, and the downstream end of the pressure sidewall meeting the suction sidewall at a location upstream from the trailing edge.
A gas turbine engine includes: a turbine blade including an inner platform; and a guide vane including an inner platform, the guide vane disposed downstream of the turbine blade, an upstream side of the inner platform of the guide vane interfacing with a downstream side of the inner platform of the turbine blade, the upstream side of the inner platform of the guide vane being longer than the downstream side of the inner platform of the turbine blade.
To easily identify the discussion of any particular element or act, the most significant digit or digits in a reference number refer to the figure number in which that element is first introduced.
Before any embodiments of the invention are explained in detail, it is to be understood that the invention is not limited in its application to the details of construction and the arrangement of components set forth in this description or illustrated in the following drawings. The invention is capable of other embodiments and of being practiced or of being carried out in various ways. Also, it is to be understood that the phraseology and terminology used herein is for the purpose of description and should not be regarded as limiting.
Various technologies that pertain to systems and methods will now be described with reference to the drawings, where like reference numerals represent like elements throughout. The drawings discussed below, and the various embodiments used to describe the principles of the present disclosure in this patent document are by way of illustration only and should not be construed in any way to limit the scope of the disclosure. Those skilled in the art will understand that the principles of the present disclosure may be implemented in any suitably arranged apparatus. It is to be understood that functionality that is described as being carried out by certain system elements may be performed by multiple elements. Similarly, for instance, an element may be configured to perform functionality that is described as being carried out by multiple elements. The numerous innovative teachings of the present application will be described with reference to exemplary non-limiting embodiments.
Also, it should be understood that the words or phrases used herein should be construed broadly, unless expressly limited in some examples. For example, the terms “including”, “having”, and “comprising” as well as derivatives thereof, mean inclusion without limitation. The singular forms “a”, “an”, and “the” are intended to include the plural forms as well, unless the context clearly indicates otherwise. Further, the term “and/or” as used herein refers to and encompasses any and all possible combinations of one or more of the associated listed items. The term “or” is inclusive, meaning and/or, unless the context clearly indicates otherwise. The phrases “associated with” and “associated therewith” as well as derivatives thereof, may mean to include, be included within, interconnect with, contain, be contained within, connect to or with, couple to or with, be communicable with, cooperate with, interleave, juxtapose, be proximate to, be bound to or with, have, have a property of, or the like. Furthermore, while multiple embodiments or constructions may be described herein, any features, methods, steps, components, etc. described with regard to one embodiment are equally applicable to other embodiments absent a specific statement to the contrary.
Also, although the terms “first”, “second”, “third” and so forth may be used herein to refer to various elements, information, functions, or acts, these elements, information, functions, or acts should not be limited by these terms. Rather these numeral adjectives are used to distinguish different elements, information, functions or acts from each other. For example, a first element, information, function, or act could be termed a second element, information, function, or act, and, similarly, a second element, information, function, or act could be termed a first element, information, function, or act, without departing from the scope of the present disclosure.
In addition, the term “adjacent to” may mean that an element is relatively near to but not in contact with a further element or that the element is in contact with the further portion, unless the context clearly indicates otherwise. Further, the phrase “based on” is intended to mean “based, at least in part, on” unless explicitly stated otherwise. Terms “about” or “substantially” or like terms are intended to cover variations in a value that are within normal industry manufacturing tolerances for that dimension. If no industry standard is available, a variation of twenty percent would fall within the meaning of these terms unless otherwise stated.
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 that air for delivery to the combustion section 104. The illustrated compressor section 102 is an example of one compressor section 102 with other arrangements and designs being possible.
In the illustrated construction, the combustion section 104 includes a plurality of separate combustors 120 that each operate to mix a flow of fuel with the compressed air from the compressor section 102 and to combust that air-fuel mixture to produce a flow of high temperature, high pressure combustion gases or exhaust gas 122. Of course, many other arrangements of the combustion section 104 are possible.
The turbine section 106 includes a plurality of turbine stages 124 with each turbine stage 124 including a number of rotating turbine blades 126 and a number of stationary turbine vanes 128. The turbine stages 124 are arranged to receive the exhaust gas 122 from the combustion section 104 at a turbine inlet 130 and expand that gas to convert thermal and pressure energy into rotating or mechanical work. The turbine section 106 is connected to the compressor section 102 to drive the compressor section 102. For gas turbine engines 100 used for power generation or as prime movers, 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 possible.
An exhaust portion 110 is positioned downstream of the turbine section 106 and is arranged to receive the expanded flow of exhaust gas 122 from the final turbine stage 124 in the turbine section 106. The exhaust portion 110 is arranged to efficiently direct the exhaust gas 122 away from the turbine section 106 to assure efficient operation of the turbine section 106. Many variations and design differences are possible in the exhaust portion 110. As such, the illustrated exhaust portion 110 is but one example of those variations.
A control system 132 is coupled to the gas turbine engine 100 and operates to monitor various operating parameters and to control various operations of the gas turbine engine 100. In preferred constructions the control system 132 is typically micro-processor 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, and the like that allow users to interface with the control system 132 to provide inputs or adjustments. In the example of a power generation system, a user may input a power output set point and the control system 132 may adjust the various control inputs to achieve that power output in an efficient manner.
The control system 132 can control various operating parameters including, but not limited to variable inlet guide vane positions, fuel flow rates and pressures, engine speed, valve positions, 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 assure that the gas turbine engine 100 is operating properly. Some parameters that are monitored may include inlet air temperature, compressor outlet temperature and pressure, combustor outlet temperature, fuel flow rate, generator power output, bearing temperature, and the like. Many of these measurements are displayed for the user and are logged for later review should such a review be necessary.
The guide vane 300 includes an inner platform 210 and an outer platform 302. The guide vane 300 includes a first vane airfoil 212 and a second vane airfoil 212 extending between the inner platform 210 and the outer platform 302. The first vane airfoil 212 and the second vane airfoil 212 are spaced apart from each other in a circumferential direction. Such an arrangement of having two vane airfoils 212 in one guide vane 300 reduces air leakage between guide vanes 300. The arrangement may thus improve performance of the gas turbine engine 100. The arrangement also reduces numbers of guide vanes 300 in the circumferential direction. The arrangement may thus also reduce manufacturing cost. In the illustrated construction, the guide vane 300 includes two vane airfoils 212. It is possible that the guide vane 300 may include more than two vane airfoils 212 or any suitable numbers of vane airfoils 212.
The front hook 402 has a general C-shape having an axially facing front side surface 406 extending in the radial direction 216. Axial or axially extending is in relation to the central axis 112 of the gas turbine engine 100. The front hook 402 includes a front inner arm 408 and a front outer arm 410 axially extending upstream from two radial ends of the front side surface 406. A front locking feature 412 is disposed on the front outer arm 410. The front locking feature 412 extends radially outward from the front outer arm 410. In the illustrated construction, the front locking feature 412 is located off the center of the front hook 402 in a circumferential direction. It is possible that the front locking feature 412 is located at the center of the front hook 402 or at any suitable locations of the front hook 402. The front locking feature 412 is a general rectangular shaped block. It is possible that the front locking feature 412 includes two separate general rectangular shaped blocks. It is also possible that the front locking feature 412 includes any suitable locking shapes.
The rear hook 404 has a similar configuration of the front hook 402. The rear hook 404 has a general C-shape having an axially facing rear side surface 414 extending in the radial direction 216. The rear hook 404 includes a rear inner arm 416 and a rear outer arm 418 axially extending downstream from two radial ends of the rear side surface 414. A rear locking feature 420 is disposed on the rear outer arm 418. The rear locking feature 420 extends radially outward from the rear outer arm 418. In the illustrated construction, the rear locking feature 420 is located at the center of the rear hook 404 in the circumferential direction. It is possible that the rear locking feature 420 is located off the center of the rear hook 404 or at any suitable locations of the rear hook 404. The rear locking feature 420 is a general rectangular shaped block. It is possible that the rear locking feature 420 includes two separate general rectangular shaped blocks. It is also possible that the rear locking feature 420 includes any suitable locking shapes.
The front locking feature 412 and the rear locking feature 420 limit the guide vane 300 from twisting. The front locking feature 412 and the rear locking feature 420 improve sealing capacity between an adjacent guide vane 300.
The inner platform 210 has a front inner rail 504 disposed at the front side of the inner platform 210 and extending radially towards the base plate 512 of the inter stage seal 502. The inner platform 210 has a rear inner rail 506 disposed at the rear side of the inner platform 210 and extending towards the base plate 512 of the inter stage seal 502. The inner platform 210, the front inner rail 504, and the rear inner rail 506 form a general U-shape toward the base plate 512. The inter stage seal 502 is coupled to the inner platform 210 by placing the front inner rail 504 within the front groove 508 and placing the rear inner rail 506 within the rear groove 510. Pins 520 are used to complete the connection between the inter stage seal 502 and the inner platform 210.
A seal (not shown in
The rear outer arm 418 of the rear hook 404 extends downstream with respect to the flow direction 214. The rear outer arm 418 may also interface with a seal disposed on an adjacent downstream component of the guide vane 600 in the gas turbine engine 100. The downstream extending rear outer arm 418 improves sealing between the guide vane 600 and the adjacent downstream component.
The borescope port 702 is attached to the outer platform 302 by brazing. The brazing is performed at a brazing area 806 between the surface of the outer wall 802 contacting the outer platform 302 and the outer platform 302. The brazing area 806 at the surface of the outer wall 802 contacting the outer platform 302 and the outer platform 302 reduces spallation of the coating 808.
It should be noted that
Although an exemplary embodiment of the present disclosure has been described in detail, those skilled in the art will understand that various changes, substitutions, variations, and improvements disclosed herein may be made without departing from the spirit and scope of the disclosure in its broadest form.
None of the description in the present application should be read as implying that any particular element, step, act, or function is an essential element, which must be included in the claim scope: the scope of patented subject matter is defined only by the allowed claims. Moreover, none of these claims are intended to invoke a means plus function claim construction unless the exact words “means for” are followed by a participle.
| Filing Document | Filing Date | Country | Kind |
|---|---|---|---|
| PCT/US2021/071347 | 9/2/2021 | WO |
| Number | Date | Country | |
|---|---|---|---|
| 63074811 | Sep 2020 | US |
