US20150159509A1

US20150159509A1 - Method and System for Dispensing Gas Turbine Anticorrosive Protection

Info

Publication number: US20150159509A1
Application number: US14/099,299
Authority: US
Inventors: Alston I. Scipio; Douglas S. Byrd; Dale J. Davis; Sanji Ekanayake
Original assignee: General Electric Co
Current assignee: General Electric Co
Priority date: 2013-12-06
Filing date: 2013-12-06
Publication date: 2015-06-11
Also published as: JP2015113840A; CH708989A8; CN104819055A; DE102014117269A1; CH708989A2

Abstract

Methods and systems for dispersing anticorrosive treatment for a turbine engine may incorporate an inlet bleed heat system. In an embodiment, a method may include selecting an anticorrosion fluid for a turbine engine and distributing the anticorrosion fluid via a vaporizing system fluidly connected with the turbine engine, wherein the vaporizing system is used to transform the anticorrosion fluid into a vapor.

Description

BACKGROUND OF THE INVENTION

A compressor of a gas turbine engine may be exposed to dust ingestion and entry of an occasional dislodged foreign object that bypasses the inlet and results in varying degree of impact damage (e.g., corrosion, tip erosion/rubs, trailing edge thinning and stator root erosion). A gas turbine engine also has blades and other structures of a turbine that are subject over time to the buildup of deposits of various residues that are byproducts of the combustion process. Impact damage and deposit build up results in loss of turbine efficiency and potential degradation of gas turbine engine components.

BRIEF DESCRIPTION OF THE INVENTION

Disclosed herein are methods and systems for dispersing turbine engine anticorrosive protection. In an embodiment, a system includes a source of an anticorrosion fluid for metal in fluid communication with a vaporizing system, the vaporizing system transforming the anticorrosion fluid into a vapor. Also the system includes a passage in fluid communication with the vaporizing system and a turbine engine in fluid communication with the passage, wherein the anticorrosion fluid is distributed to the turbine engine via the passage.
In an embodiment, a method may include selecting an anticorrosion fluid for a turbine engine and distributing the anticorrosion fluid via a vaporizing system fluidly connected with the turbine engine, wherein the vaporizing system is used to transform the anticorrosion fluid into a vapor.
In an embodiment, a system may include a processor adapted to execute computer-readable instructions and a memory communicatively coupled to the processor. The memory may have stored therein computer-readable instructions that, if executed by the processor, cause the processor to perform operations including selecting an anticorrosion fluid for a turbine engine and providing instructions to distribute the anticorrosion fluid via a vaporizing system fluidly connected with the turbine engine, wherein the vaporizing system transforms the anticorrosion fluid into a vapor.
This Brief Description of the Invention is provided to introduce a selection of concepts in a simplified form that are further described below in the Detailed Description. This Brief Description of the Invention is not intended to identify key features or essential features of the claimed subject matter, nor is it intended to be used to limit the scope of the claimed subject matter. Furthermore, the claimed subject matter is not limited to limitations that solve any or all disadvantages noted in any part of this disclosure.

BRIEF DESCRIPTION OF THE DRAWINGS

A more detailed understanding may be had from the following description, given by way of example in conjunction with the accompanying drawings wherein:

FIG. 1 is a sectional view of a gas turbine engine including turbine and compressor piping;

FIG. 2 is an exemplary illustration of a power plant system;

FIG. 3 illustrates a non-limiting, exemplary method of applying a gas turbine anticorrosive treatment;

FIG. 4 illustrates a non-limiting, exemplary method of applying a gas turbine anticorrosive treatment; and

FIG. 5 is an exemplary block diagram representing a general purpose computer system in which aspects of the methods and systems disclosed herein or portions thereof may be incorporated.

DETAILED DESCRIPTION OF THE INVENTION

Disclosed herein are methods and systems of dispersing an anticorrosion fluid for a gas turbine, such as a polyamine based fluid. In an embodiment, existing inlet bleed heat (IBH) piping in combination with a bleed heat dispensing manifold may be utilized as a means of communicating and dispensing the anticorrosion fluid for imparting anti-corrosion protection.
As used herein, the term “polyamine” is used to refer to an organic compound having two or more primary amino groups —NH2. In an embodiment, an anticorrosion agent may comprise a volatile neutralizing amine which neutralizes acidic contaminants and elevates the pH into an alkaline range, and with which protective metal oxide coatings are particularly stable and adherent. Non-limiting examples of the anticorrosion agent include cycloheaxylamine, morpholine, monoethanolamine, N-9-Octadecenyl-1,3-propanediamine, 9-octadecen-1-amine, (Z)-1-5, dimethylaminepropylamine (DMPA), diethylaminoethanol (DEAE), and the like, and a combination comprising at least one of the aforementioned. For example, anticorrosion fluid may include a combination of a polyamine (a multifunction organic amine corrosion inhibitor) and neutralizing amines (volatile organic amines). Different ratio blends of the anticorrosion fluid may be introduced by varying the valve alignment.
In an embodiment, appropriate logic may be enabled to ensure that the anticorrosion fluid cannot be excessively utilized to impart power augmentation, NOx abatement, or grid frequency support, among other things. The application of the anticorrosion fluid may be based on one or more conditions such as, environmental conditions, rate of degradation, gas turbine engine frame size, type of wash performed, duration of wash, or a borescope inspection, among other things.
FIG. 1 is an exemplary illustration of a gas turbine engine 11 that includes cooling and sealing air valve and pipe components. Compressor 15 may include a number of stages. As shown in FIG. 1, there may be an A-stage 54, a B-stage 55, or C-stage 56 of the compressor. The terms “A-stage”, “X-stage”, and the like are used herein as opposed to “first stage”, “second stage,” and the like so as to prevent an inference that the systems and methods described herein are in any way limited to use with the actual first stage or the second stage of the compressor or the turbine. Any number of the stages may be used. Each stage includes a number of circumferentially arranged rotating blades, such as blade 59, blade 60, and blade 61. Any number of blades may be used. The blades may be mounted onto a rotor wheel 65. The rotor wheel 65 may be attached to the power output drive shaft for rotation therewith. Each stage also may include a number of circumferentially arranged stationary vanes 67. Any number of the vanes 67 may be used. The vanes 67 may be mounted within an outer casing 70. The casing 70 may extend from a bellmouth 75 towards turbine 17. The flow of air 22 enters the compressor 15 about the bellmouth 75 and is compressed through the blades (e.g., blade 59, 60, and 61, among others) and the vanes 67 of the stages before flowing to the combustor.
FIG. 2 is an exemplary illustration of a power plant system 105. In normal operation, inlet air flows into the inlet filter house 110 via the inlet hoods 114, and through a plurality of filter elements. The filtered inlet air passes through an air duct (inlet duct) or passage 112 to a gas turbine engine 116. Passage 112 may contain an inlet bleed heating manifold 111. Gas turbine engine 116 includes a compressor section 117, a combustion section 118, and a turbine section 119. High pressure air from compressor section 117 enters combustion section 118 of the gas turbine engine 116 where the air is mixed with fuel and burned.
As illustrated in FIG. 2, inlet bleed heat (IBH) piping 124 is connected with the IBH manifold 111. IBH piping 124 is fluidly connected with anticorrosion fluid piping 122 which is connected with a anticorrosion fluid source 120. Inlet bleed heat (IBH) may be used to protect the gas turbine engine compressor from icing when operating or optimized to enhance operationally or to reduce compressor pressure ratio at certain operating conditions where additional compressor operating margin is required. This method of gas turbine engine operation, known as IBH control, raises the inlet temperature of the compressor inlet air by mixing the colder ambient air with the bleed portion of the hot compressor discharge air, thereby reducing the air density and the mass flow to the gas turbine engine. IBH piping 124 and IBH manifold 111 is traditionally located downstream of the inlet air filters.
In an embodiment, an anticorrosion fluid may include a mixture of a polyamine based fluid and water. The anticorrosion fluid may be of a predetermined ratio of anticorrosion agents, water, or other fluids. The anticorrosion fluid may be inserted into the IBH piping 124 via anticorrosion fluid piping 122. The water-polyamine mixture may be transformed to a vapor (e.g., steam) by the IBH system. The IBH system acts as a vaporizing system to vaporize the anticorrosion fluid. The anticorrosion fluid may travel through air duct 112 and into the compressor bellmouth. There may be an assortment of valves, mixing chambers, sensors, controls, or the like, as discussed and implied herein, that help determine and execute the use of the anticorrosion fluid. The use of IBH piping 124 to help administer a anticorrosion fluid may be done while the gas turbine engine is in normal online operation, during an online wash, or after an offline wash. It is also contemplated herein that another device may be used to assist or create a vapor anticorrosion fluid. For example, another device, alone or in combination with the IBH system, may increase the anticorrosion fluid temperature in order to create the vapor. In another embodiment, anticorrosion fluid may be supplied from an independent and external source, such as a tanker truck. The external source can be manually connected via quick disconnect provisions on anticorrosion fluid piping 122 connected with the IBH piping 124.
Anticorrosion fluid may be dispersed via IBH manifold 111 when gas turbine engine 116 is offline or online. Gas turbine engine 116 may be considered offline when the machine is operating at significantly below normal power generating output level. Whether gas turbine engine 116 is online may be determined based on power output level, but usually includes the gas turbine engine 116 operating at higher temperatures (e.g., turbine operating above 145° F.). During an offline wash gas turbine engine 116 may be cooled down, until the interior volume and surfaces have cooled down sufficiently (e.g., around 145° F.) so that a water or cleaning mixture being introduced into the gas turbine engine will not thermally shock the internal metal and induce creep, or induce any mechanical or structural deformation of the material.
In an embodiment, just water and one or more anticorrosion agents may be mixed in a predetermined ratio. A water-anticorrosion agent mixture may be held in a separate storage tank (e.g., a premixed anticorrosion fluid). The mixture for the resulting anticorrosion fluid may be based on the gas turbine engine frame size, duration of wash in combination with discharge, or flow requirement. The ratio also may be adjusted based on the type of amine.
Once mixed the anticorrosion fluid may be dispersed to create a molecular layer coating-a micro-coating on metal. Metal passivation imparts a protective shield to metal and/or metal alloy substrates from environmental factors (e.g., high temperatures, combustion by-products, debris, etc.) exhibited in gas turbine engines by forming a coating (e.g., a metal oxide layer) which protects the metal or metal alloy substrate from corrosive species. In an embodiment, the coating that results from the application of the anticorrosion fluid may serve to strengthen the bonds in the metal or metal alloy substrate of a compressor, such as compressor 117. Based on the mixture of the anticorrosion fluid (e.g., type of anticorrosion agents), significant thermal decomposition of the anticorrosion coating may not be exhibited until temperatures above 500° C. is reached. In an embodiment, successive anticorrosion treatment cycles may be applied to the compressor 117 using the systems described herein, resulting in a multi-layer anticorrosion coating.
Anticorrosion fluid may impart corrosion resistance and/or inhibition to compressor 117 by using metal passivation to provide an anticorrosion coating on the metal and/or metal alloy substrates in a gas turbine engine with which the anticorrosion mixture comes into contact via the entry points at the IBH manifold 111, before compressor 117, as discussed herein. Resultant anticorrosion fluid (partially or fully) coats stages of compressor 117 of gas turbine engine and various metallic components therein (e.g., compressor blades and stator vanes).
The anticorrosion fluid may comprise water and an anticorrosion agent in a particularly selected, predetermined ratio. Any anticorrosion agent that is suitable to impart an anticorrosive coating in a gas turbine engine may be employed. In an embodiment, the anticorrosion agent is an organic amine, which acts as a corrosion inhibitor by adsorbing at the metal/metal oxide surface of components in the gas turbine engine, thereby restricting the access of potentially corrosive species (e.g., dissolved oxygen, carbonic acid, chloride/sulfate anions, etc.) to the metal or metal alloy substrate surface of the gas turbine engine component. In an embodiment, the anticorrosion agent is two or more organic amines. In an embodiment, the anticorrosion inhibitor is a polyamine. In an embodiment, anticorrosion treatment may include a combination of polyamine and neutralizing amines.
Referring to FIG. 2, valving (not shown) connected with piping 122 may enable selection between different sources of anticorrosion agents or fluids based on application of the fluid to the compressor 117. The anticorrosion fluid may be steam. Anticorrosion fluid may be supplied from an external source, e.g., a truck, and may be manually connected via the quick disconnects as disclosed herein. The anticorrosion fluid may be mixed automatically at a predetermined ratio (adjustable based on the type of amine) and dispersed thereafter. Inlet and drain valves may be optimally positioned and aligned prior to introduction of the anticorrosion fluid.
Power plant system 105 may incorporate a plurality of sensors (not shown) such as a motor sensor, a fluid level sensor, a fluid pressure sensor, a mixture outflow pressure sensor, a compressor pressure sensor which senses pressure in a compressor section of a gas turbine engine, a turbine pressure sensor which senses pressure in gas turbine engine 116, or valve position sensors, among other sensors. Power plant system 105 may further include flow sensors configured to sense the rate of flow of a fluid flowing (or not flowing) through piping.
FIG. 3 illustrates a non-limiting exemplary method 400 of applying an anticorrosion fluid to a gas turbine engine. In an embodiment, at step 405, an anticorrosion fluid may be selected. The anticorrosion fluid may be selected from known anticorrosion fluids for metals. At step 410, the anticorrosion fluid may be vaporized by an IBH system. At step 415, the anticorrosion fluid may be distributed to the gas turbine engine. The inlet bleed heat manifold is usually located in a duct between air intake filters and a compressor of the gas turbine engine. The flow of air in the duct towards the gas turbine engine assists in the distribution of the anticorrosion fluid to the compressor of the gas turbine engine.
FIG. 4 illustrates a non-limiting, exemplary method 500 of applying an anticorrosion fluid to a gas turbine engine. In an embodiment at step 505, the condition of the gas turbine engine (e.g., compressor or turbine) may be determined. The condition may be determined based on sensors, borescope inspection, or the like. The condition may include whether the compressor or turbine is clean and pretreated (e.g., amount of debris or dust), whether a gas turbine engine is in operation (e.g., offline or online), how long the gas turbine engine has been in operation, or turbine output, among other things. The condition of whether the gas turbine engine is clean may be determined by data from fouling sensors, the elapsed time between cleanings, or atmospheric conditions during the operation of the gas turbine engine, among other things.
At step 510, the type of anticorrosion fluid to apply to the gas turbine engine may be determined based on the condition of the gas turbine engine. The condition of the gas turbine engine may include the type of gas turbine engine, the operating environment, the amount of damage to the gas turbine engine, the temperature of the gas turbine engine, the power out level of the gas turbine engine, or the like.
At step 515, a anticorrosion fluid may be applied to the gas turbine engine based on the condition of the gas turbine engine. If a compressor, turbine, or other gas turbine engine component is dirty when a anticorrosion fluid is applied, the anticorrosion fluid may not bond properly to the gas turbine engine components which in turn, may reduce the effectiveness of the applied anticorrosion fluid. In an embodiment, aerosolized anticorrosion fluid may be applied after cleaning of a gas turbine engine. The cleaning may include one or more of the following: the utilization of a detergent and demineralized water for compressor washing; utilization of an “intra Rinse” solution or pre-passivating treatment followed by a neutralizing rinse.
In an exemplary embodiment, control system 190 communicates, via wireless or hardwired, with the sensors described herein, and further communicates with actuation mechanisms (not shown) provided to start, stop, or control the speed of motors. The control system may open, close, or regulate the position of valves used to accomplish the operations of power plant system 105, as described herein.
Control system 190, as shown in FIG. 2, may be a computer system that is communicatively connected with a panel/display. Control system 190 may execute programs to control the operation of power plant system 105 using sensor inputs and instructions from human operators via human machine interface (HMI) terminals. In addition, in an exemplary embodiment, control system 190 may be programmed to alter (or restrict) the ratio of water to polyamine or other agent, alter (or restrict) the cycle times for wash sequences, or alter (or restrict) the order of steps in wash or rinse cycles, or alter the order or restrict the duration of the anticorrosion fluid dispensation.
Control system 190 is communicatively connected with power plant systems and devices. Once all the predetermined logic permissive for the application of the anticorrosion fluid has been met, the online wash/treatment using the anticorrosion fluid may become active and the anticorrosion fluid may be appropriately applied. Control system 190 may automatically run the gas turbine engine based on a predetermined/predesigned sequence specifically designed for anticorrosion fluid dispensing operating mode. The method for online wash/treatment system activation and operation includes determining that the power output and other turbine control parameters have been satisfied for online application/dispensation. Control system 190 may attempt to maintain a substantially constant air flow from the compressor to facilitate controlling a fuel to compressor discharge pressure ratio such that a combustor state does not lag changes in airflow during the wash sequence. During operation this system will have the effect of increasing the “mass flow” through the turbine thereby permitting an increase in power delivered to the grid. With the aforementioned in mind, control system 190 may be configured with the appropriate checks and limitations to ensure that it cannot be used excessively (e.g., abused) for power augmentation, NOx abatement, or grid frequency support.
In an embodiment, during the application of the anticorrosion fluid (e.g., via online washing, via inlet bleed heat system, evaporative cooling system, etc.), control system 190 may be configured to provide instructions to systems that help control gas turbine engine 116 to maintain an appropriate power output level. An appropriate power level may be manually set, determined by analysis of the current or similar gas turbine engines, or the like. In an embodiment, excessive use may be minimized by restrictive access to change online anticorrosion fluid dispersion control logic. For example, minimal access to change the polyamine water ratio for online anticorrosion fluid dispersion, minimal access to change cycle time for anticorrosion fluid dispersion sequences (e.g., between dispersals), minimal access to change cycle time for online anticorrosion fluid dispersion (e.g., during a dispersal), or the like. Abuse of the online anticorrosion fluid dispersion or other application of the anticorrosion fluid may be indicated by patterns in the frequency and other data, as suggested herein, with regard to the application of the anticorrosion fluid.
Without in any way limiting the scope, interpretation, or application of the claims appearing herein, a technical effect disclosed herein is the utilization of a combination of chemicals (i.e., corrosion inhibitors) in a ratio of acid and alkaline chemicals in temperature supportive environmental conditions to help the formation of a passivation layer on the surface of the gas turbine engine compressor blades and stator vanes. The ratio may be predetermined. Corrosion mitigation may help maintain recovered performance for a longer duration. The application of the corrosion inhibitor may reduce the propensity for compressor blade or turbine blade erosion from numerous water washes. Integrating the anticorrosion distribution system into the inlet bleed heat system, and other existing systems, such as the systems discussed herein, may minimize a need for new extensive piping runs or casing penetrations.
FIG. 5 and the following discussion are intended to provide a brief general description of a suitable computing environment in which the methods and systems disclosed herein and/or portions thereof may be implemented. Although not required, portions of the methods and systems disclosed herein is described in the general context of computer-executable instructions, such as program modules, being executed by a computer, such as a client workstation, server, personal computer, or mobile computing device such as a smartphone. Generally, program modules include routines, programs, objects, components, data structures and the like that perform particular tasks or implement particular abstract data types. Moreover, it should be appreciated the methods and systems disclosed herein and/or portions thereof may be practiced with other computer system configurations, including hand-held devices, multi-processor systems, microprocessor-based or programmable consumer electronics, network PCs, minicomputers, mainframe computers and the like. A processor may be implemented on a single-chip, multiple chips or multiple electrical components with different architectures. The methods and systems disclosed herein may also be practiced in distributed computing environments where tasks are performed by remote processing devices that are linked through a communications network. In a distributed computing environment, program modules may be located in both local and remote memory storage devices.
FIG. 5 is a block diagram representing a general purpose computer system in which aspects of the methods and systems disclosed herein and/or portions thereof may be incorporated. As shown, the exemplary general purpose computing system includes a computer 620 or the like, including a processing unit 621, a system memory 622, and a system bus 623 that couples various system components including the system memory to the processing unit 621. The system bus 623 may be any of several types of bus structures including a memory bus or memory controller, a peripheral bus, and a local bus using any of a variety of bus architectures. The system memory includes read-only memory (ROM) 624 and random access memory (RAM) 625. A basic input/output system 626 (BIOS), containing the basic routines that help to transfer information between elements within the computer 620, such as during start-up, is stored in ROM 624.
The computer 620 may further include a hard disk drive 627 for reading from and writing to a hard disk (not shown), a magnetic disk drive 628 for reading from or writing to a removable magnetic disk 629, and an optical disk drive 630 for reading from or writing to a removable optical disk 631 such as a CD-ROM or other optical media. The hard disk drive 627, magnetic disk drive 628, and optical disk drive 630 are connected to the system bus 623 by a hard disk drive interface 632, a magnetic disk drive interface 633, and an optical drive interface 634, respectively. The drives and their associated computer-readable media provide non-volatile storage of computer readable instructions, data structures, program modules and other data for the computer 620. As described herein, computer-readable media is a tangible, physical, and concrete article of manufacture and thus not a signal per se.
Although the exemplary environment described herein employs a hard disk, a removable magnetic disk 629, and a removable optical disk 631, it should be appreciated that other types of computer readable media which can store data that is accessible by a computer may also be used in the exemplary operating environment. Such other types of media include, but are not limited to, a magnetic cassette, a flash memory card, a digital video or versatile disk, a Bernoulli cartridge, a random access memory (RAM), a read-only memory (ROM), and the like.
A number of program modules may be stored on the hard disk, magnetic disk 629, optical disk 631, ROM 624 or RAM 625, including an operating system 635, one or more application programs 636, other program modules 637 and program data 638. A user may enter commands and information into the computer 620 through input devices such as a keyboard 640 and pointing device 642. Other input devices (not shown) may include a microphone, joystick, game pad, satellite disk, scanner, or the like. These and other input devices are often connected to the processing unit 621 through a serial port interface 646 that is coupled to the system bus, but may be connected by other interfaces, such as a parallel port, game port, or universal serial bus (USB). A monitor 647 or other type of display device is also connected to the system bus 623 via an interface, such as a video adapter 648. In addition to the monitor 647, a computer may include other peripheral output devices (not shown), such as speakers and printers. The exemplary system of FIG. 6 also includes a host adapter 655, a Small Computer System Interface (SCSI) bus 656, and an external storage device 662 connected to the SCSI bus 656.
The computer 620 may operate in a networked environment using logical connections to one or more remote computers, such as a remote computer 649. The remote computer 649 may be a personal computer, a server, a router, a network PC, a peer device or other common network node, and may include many or all of the elements described above relative to the computer 620, although only a memory storage device 650 has been illustrated in FIG. 5. The logical connections depicted in FIG. 5 include a local area network (LAN) 651 and a wide area network (WAN) 652. Such networking environments are commonplace in offices, enterprise-wide computer networks, intranets, and the Internet.
When used in a LAN networking environment, the computer 620 is connected to the LAN 651 through a network interface or adapter 653. When used in a WAN networking environment, the computer 620 may include a modem 654 or other means for establishing communications over the wide area network 652, such as the Internet. The modem 654, which may be internal or external, is connected to the system bus 623 via the serial port interface 646. In a networked environment, program modules depicted relative to the computer 620, or portions thereof, may be stored in the remote memory storage device. It will be appreciated that the network connections shown are exemplary and other means of establishing a communications link between the computers may be used.
Computer 620 may include a variety of computer readable storage media. Computer readable storage media can be any available media that can be accessed by computer 620 and includes both volatile and nonvolatile media, removable and non-removable media. By way of example, and not limitation, computer readable media may comprise computer storage media and communication media. Computer storage media include both volatile and nonvolatile, removable and non-removable media implemented in any method or technology for storage of information such as computer readable instructions, data structures, program modules or other data. Computer storage media include, but are not limited to, RAM, ROM, EEPROM, flash memory or other memory technology, CD-ROM, digital versatile disks (DVD) or other optical disk storage, magnetic cassettes, magnetic tape, magnetic disk storage or other magnetic storage devices, or any other medium which can be used to store the desired information and which can be accessed by computer 620. Combinations of any of the above should also be included within the scope of computer readable media that may be used to store source code for implementing the methods and systems described herein. Any combination of the features or elements disclosed herein may be used in one or more embodiments.
In describing embodiments of the subject matter of the present disclosure, as illustrated in the Figures, specific terminology is employed for the sake of clarity. The claimed subject matter, however, is not intended to be limited to the specific terminology so selected, and it is to be understood that each specific element includes all technical equivalents that operate in a similar manner to accomplish a similar purpose. An aerosolized anticorrosion fluid, a vapor anticorrosion fluid, or a non-aerosolized liquid anticorrosion fluid may be implemented. Although a gas turbine engine for a power plant system is discussed, other similar turbine engine configurations are contemplated herein. The anticorrosion fluid discussed herein may be applied simultaneously via different systems, such as an inlet bleed heat system, evaporative cooling system, bellmouth nozzle, extraction piping, or other devices. Any combination of the features or elements disclosed herein with regard to an anticorrosion fluid may be used in one or more embodiments.
This written description uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the invention is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they have structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal languages of the claims.

Claims

What is claimed:

1. A system comprising:

a source of an anticorrosion fluid for metal in fluid communication with a vaporizing system, the vaporizing system used to transform the anticorrosion fluid into a vapor;

a passage in fluid communication with the vaporizing system; and

a turbine engine in fluid communication with the passage, wherein the anticorrosion fluid is distributed to the turbine engine via the passage.

2. The system of claim 1, wherein the vaporizing system is an inlet bleed heat system.

3. The system of claim 2, wherein the inlet bleed heat system comprises an inlet bleed heat manifold or inlet bleed heat piping.

4. The system of claim 1, wherein the anticorrosion fluid is a polyamine based fluid.

5. The system of claim 1, wherein the turbine engine includes a compressor section or a turbine section.

6. The system of claim 1, wherein the anticorrosion fluid is applied while the turbine engine is offline.

7. The system of claim 1, further comprising:

a mixing chamber in fluid communication with the source of the anticorrosion fluid.

8. The system of claim 7, further comprising:

a source of water in fluid communication with the mixing chamber, wherein the mixing chamber mixes an anticorrosion agent with the water to make the anticorrosion fluid, wherein the anticorrosion agent is selected based on a condition of the turbine engine.

9. The system of claim 8, wherein the condition of the turbine engine comprises at least one of a power output level of the turbine engine, elapsed time between applying the anticorrosion fluid, elapsed operation time of the turbine engine, temperature of the turbine engine, or atmospheric conditions near the turbine engine during operation.

10. The system of claim 1, wherein the anticorrosion fluid is selected from a group of anticorrosion fluids based on a condition of the turbine engine.

11. A method comprising:

selecting an anticorrosion fluid for a turbine engine; and

distributing the anticorrosion fluid via a vaporizing system fluidly connected with the turbine engine, the vaporizing system used to transform the anticorrosion fluid into a vapor.

12. The method of claim 11, wherein the anticorrosion fluid is a polyamine based fluid.

13. The method of claim 11, further comprising:

distributing the anticorrosion fluid via a bellmouth injection nozzle near a compressor of the turbine engine.

14. The method of claim 11, further comprising:

creating the anticorrosion fluid by mixing an anticorrosion agent with water at a set ratio based on a condition of the turbine engine.

15. The method of claim 11, wherein the anticorrosion fluid is created from combining at least two of the following: cycloheaxylamine, morpholine, monoethanolamine, N-9-Octadecenyl-1,3-propanediamine, 9-octadecen-1-amine, (Z)-1-5, dimethylaminepropylamine (DMPA), diethylaminoethanol (DEAE), or polyamine.

16. A system comprising:

a processor adapted to execute computer-readable instructions; and

a memory communicatively coupled to said processor, said memory having stored therein computer-readable instructions that, if executed by the processor, cause the processor to perform operations comprising:

providing instructions to select an anticorrosion fluid for a turbine engine; and

providing instructions to distribute the anticorrosion fluid via a vaporizing system fluidly connected with the turbine engine, the vaporizing system used to transform the anticorrosion fluid into a vapor.

17. The system of claim 16, wherein the anticorrosion fluid is a polyamine based fluid.

18. The system of claim 16, wherein the vaporizing system comprises an inlet bleed heat system.

19. The system of claim 16, wherein the inlet bleed heat system comprises an inlet bleed heat manifold or inlet bleed heat piping.

20. The system of claim 16, wherein the anticorrosion fluid was created from combining at least two of the following: water, cycloheaxylamine, morpholine, monoethanolamine, N-9-Octadecenyl-1,3-propanediamine, 9-octadecen-1-amine, (Z)-1-5, dimethylaminepropylamine (DMPA), diethylaminoethanol (DEAE), or polyamine.