WO2020018056A2 - Cooling of gas turbine engines with water recirculation - Google Patents

Cooling of gas turbine engines with water recirculation Download PDF

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Publication number
WO2020018056A2
WO2020018056A2 PCT/TR2019/050543 TR2019050543W WO2020018056A2 WO 2020018056 A2 WO2020018056 A2 WO 2020018056A2 TR 2019050543 W TR2019050543 W TR 2019050543W WO 2020018056 A2 WO2020018056 A2 WO 2020018056A2
Authority
WO
WIPO (PCT)
Prior art keywords
water
cooling
gas turbine
turbine
turbine engines
Prior art date
Application number
PCT/TR2019/050543
Other languages
French (fr)
Other versions
WO2020018056A3 (en
Inventor
Talat UYANIK
Original Assignee
Uyanik Talat
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Uyanik Talat filed Critical Uyanik Talat
Publication of WO2020018056A2 publication Critical patent/WO2020018056A2/en
Publication of WO2020018056A3 publication Critical patent/WO2020018056A3/en

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2210/00—Working fluids
    • F05D2210/10—Kind or type
    • F05D2210/11—Kind or type liquid, i.e. incompressible
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/60—Shafts
    • F05D2240/61—Hollow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/60—Shafts
    • F05D2240/63—Glands for admission or removal of fluids from shafts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/213—Heat transfer, e.g. cooling by the provision of a heat exchanger within the cooling circuit
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/232—Heat transfer, e.g. cooling characterized by the cooling medium

Definitions

  • This invention relates generally to gas turbine engines and, more particularly, to the water cooling of high and low speed turbine discs and the blades.
  • the thrust to turn the turbine blades is createdusing the energy generated by combining the compressed air from the high speed compressor with the fuel mixture inside the combustor, however, the turbine blades are required to be cooled down because the high temperature of about 1700 degrees Celsius which occurs withincombustor, as the metal alloy turbine blades cannot withstand such high heat.
  • the best known technique is to cool the turbine blades with high speed compressor air using film technique. If we consider the fact that the cooling air required for internal cooling of the turbine blades is the 20% of the air taken from the high-speed compressor (core engine), it is easy to understand how important this amount of air is to obtain power from the turbine. As the 20% of the compressor air (the core engine) is actually used for cooling, the compressor air cannot be fully utilized.
  • Cooling the low speed turbine blades using the film cooling technique is a very stressful and power wasting technique.
  • this cooling technique the stress generated when the compressed air of the high speed compressor hits the rotating HPT turbine blade, and the reduction of turbine rotation speed as a result of this cannot be ignored in physical terms. This impact, according to my estimations, causes between 5 to 10% of reduction in the rotation speed of the HPT turbine blades.
  • the aim is to cool the HPT and LPT turbine blades from the 1700 degrees Celsius heat generated by the burning of the fuel within the combustor, using water cooling systems, instead of air cooling using the 650-850 degrees Celsius air taken from the compressor,
  • water cooling systems instead of air cooling using the 650-850 degrees Celsius air taken from the compressor
  • the problems such as the loss of speed of the HPT blades during the cooling process as well as the 20% compressed air used while cooling the HPT blades of the HPC compressor and the stress caused by this air on the HPT.
  • Diagram 1 The cooling scheme of the HPT and LPT turbine disc and blades with the introduction of a water recirculation pump at the entrance of the turbofan engine main shaft by extending it into a wider funnel shape.
  • Diagram 2 Water Recirculation pump shaft diagram
  • Diagram 3 Front view diagram of main shaft input
  • Diagram 5 Connection diagram for the water recirculation pump chassis to the engine chassis externally and the R1 bearing to the inner front side of the main shaft internally
  • Diagram 6 Cross-sectional diagram showing the connection of the main shaft parts to the inner shaft
  • Diagram 7 Diagram showing connection of main shaft and intermediate shaft part to inner shaft and direction of water flow to HPT and LPT discs.
  • Diagram 8 Diagram showing the discharge of water from the shaft through the HPT Discs to the blades and from the blades to the discharge setup
  • the 4 U channels (5) on one side of the Water Recirculation pump shaft (2) are for fixing to the main shaft (7).
  • FIG 3 it is the cross-sectional front view of the water circulation pump shaft (2) connecting to the main shaft (7).
  • the water recirculation pump shaft (2), and the inlet portion of the engine main shaft (7) is secured to the four tabs (6) connected to the water recirculation pump (1) chassis (3).
  • the outside of the water recirculation pump housing (3) is fixed to the outside of the engine chassis (19) and the inside of the housing (3) is fixed to the inside of the bearing (Rl) at the inlet of the main shaft (7).
  • FIG. 8 shows a cross-sectional view of the HPT disc (8) and its blade 12, with cold water flowing through the HPT disc (8) into (10) the turbine blade (12), through which the entire blades are joined from the top into the space in the U-shaped circle.
  • Each end of the two ends of the U-ring is secured to the inside of the water-tight sealed bearing (R4, R5) to prevent water leakage. Since there is no weight on the bearings (R4, R5), there cannot be any speed loss of the rotational speed or stress over the HPT disc. Since the water cycle and cooling cycle are the same as the engine speed, the cooling is done using the cool air coming from the blades into the engine chassis, which provides a very good heat transfer, thus, the efficient cooling of the blades and discs are ensured.
  • the technical problems in the cooling process of the known Gas Turbine engines described above can be solved more successfully than the conventional techniques, with the External Gas Turbine water recirculation cooling technique.
  • the invention is a product that can be produced in the industry using a design and manufacturing study in accordance with the invention. There is no complicated process in the manufacturing of the product and impeding the working order.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The cooling of the turbine disc blades of Turbofan Gas Turbine engines can be achieved much more efficiently and cheaply, via adding a water recirculating pump (1) over the inlet of the second shaft which can be added to the engine main shaft (7), using a film cooling technique, by realizing the heat transfer as fast as the engine rotary speed or even faster, by flowing the water within the HPT (8) and LPT (9) turbine disc blades (12,13), instead of taking the compressor air which is 650-900 degrees Celsius and reduce the engine power, causing stresses and extra energy consumption.

Description

COOLING OF GAS TURBINE ENGINES WITH WATER RECIRCULATION
THE TECHNICAL FIELD TO WHICH THE INVENTION RELATES
This invention relates generally to gas turbine engines and, more particularly, to the water cooling of high and low speed turbine discs and the blades.
THE CURRENT STATUS OF THE TECHNIQUE
In known gas turbine turbofan engines, the thrust to turn the turbine blades is createdusing the energy generated by combining the compressed air from the high speed compressor with the fuel mixture inside the combustor, however, the turbine blades are required to be cooled down because the high temperature of about 1700 degrees Celsius which occurs withincombustor, as the metal alloy turbine blades cannot withstand such high heat. The best known technique is to cool the turbine blades with high speed compressor air using film technique. If we consider the fact that the cooling air required for internal cooling of the turbine blades is the 20% of the air taken from the high-speed compressor (core engine), it is easy to understand how important this amount of air is to obtain power from the turbine. As the 20% of the compressor air (the core engine) is actually used for cooling, the compressor air cannot be fully utilized. Cooling the low speed turbine blades using the film cooling technique is a very stressful and power wasting technique. In this cooling technique, the stress generated when the compressed air of the high speed compressor hits the rotating HPT turbine blade, and the reduction of turbine rotation speed as a result of this cannot be ignored in physical terms. This impact, according to my estimations, causes between 5 to 10% of reduction in the rotation speed of the HPT turbine blades. TECHNICAL PROBLEMS THAT ARE AIMED TO BE SOLVED WITH THE INVENTION
With this invention, the aim is to cool the HPT and LPT turbine blades from the 1700 degrees Celsius heat generated by the burning of the fuel within the combustor, using water cooling systems, instead of air cooling using the 650-850 degrees Celsius air taken from the compressor, With this technique, it is aimed to solve the problems such as the loss of speed of the HPT blades during the cooling process as well as the 20% compressed air used while cooling the HPT blades of the HPC compressor and the stress caused by this air on the HPT. There are two basic physical properties that make water cooling superior to air cooling. The first is that the thermal conductivity of the water is 25 times higher than of the air, and the second feature is that the heat carrying capacity of the water is 4 times higher than the air. It requires four times more heat energy to increase its temperature. Water Cooling Technique for Gas Turbine Engine blades is shown in the following diagrams.
DESCRIPTION OF THE FIGURES
Diagram 1: The cooling scheme of the HPT and LPT turbine disc and blades with the introduction of a water recirculation pump at the entrance of the turbofan engine main shaft by extending it into a wider funnel shape.
Diagram 2: Water Recirculation pump shaft diagram
Diagram 3: Front view diagram of main shaft input
Diagram 4: Water recirculation pump shaft and main shaft connection diagram
Diagram 5: Connection diagram for the water recirculation pump chassis to the engine chassis externally and the R1 bearing to the inner front side of the main shaft internally Diagram 6: Cross-sectional diagram showing the connection of the main shaft parts to the inner shaft
Diagram 7: Diagram showing connection of main shaft and intermediate shaft part to inner shaft and direction of water flow to HPT and LPT discs. Diagram 8: Diagram showing the discharge of water from the shaft through the HPT Discs to the blades and from the blades to the discharge setup
REFERENCE NUMBERS
The descriptions of the numbers in the diagrams are given below:
1: Water recirculation Pump blade
2: Water recirculation pump shaft
3: Water recirculation pump chassis
4: Bearing (Rl, R2, R3, R4, R5, R6, R7)
5: U channel (4 Pieces)
6: Tab (4 quotes)
7: Main shaft,
7- a) Intermediate shaft
7-b) Main and intermediate shaft fixing inner shaft
8: HPT Disc (High Pressure Turbine)
9: LPT Disc (Low Pressure Turbine)
10: HPT Water flow channel
11: LPT Water flow channel
12: HPT blade
13: LPT blade
14: Water Cooling Pipe (Radiator)
15: HPT hot water discharge apparatus
16: LPT hot water discharge apparatus
17: HPT cold water inlet gap
18: LPT cold water inlet gap
19: Engine protection chassis
20: LPC Compressor blade (2 stages) 21: Cold water channel.
DETAILED DESCRIPTION OF THE INVENTION
Referring to figure 1, for a Turbofan Gas Turbine engine, 4 shaft retaining tabs (6) are fixed horizontally from the inside of the main shaft (7) by inserting into the 4 U channels (5) on the water pump shaft (2). The water recirculation pump (1) passes through the main shaft (7) through the cold water inlet gap (17, 18) to the turbine disc water channel (10,11) and to the LPT and HPT blades. The water in the blades (12, 13) passes from the discharge apparatus (15, 16) to the water cooling pipes (14) which act as radiators and is cooled by the cold air flow sucked by the LPC compressor.
Referring to figure 2, the 4 U channels (5) on one side of the Water Recirculation pump shaft (2) are for fixing to the main shaft (7).
Referring to figure 3, it is the cross-sectional front view of the water circulation pump shaft (2) connecting to the main shaft (7).
Referring to figure 4, the way in which the water circulation pump shaft (2) is fixed to the main shaft (7) is shown.
Referring to figure 5, the water recirculation pump shaft (2), and the inlet portion of the engine main shaft (7) is secured to the four tabs (6) connected to the water recirculation pump (1) chassis (3). The outside of the water recirculation pump housing (3) is fixed to the outside of the engine chassis (19) and the inside of the housing (3) is fixed to the inside of the bearing (Rl) at the inlet of the main shaft (7).
Referring to figure 6, the intermediate shaft (7a) and inner shaft (7b) connections and four water channels that ensure the cold water flow (21) can be seen. Referring to Fig. 7, the main shaft (7), intermediate shaft (7-a) and inner shaft (7-b) connections and the water passage gap (17,18) are shown.
Figure 8 shows a cross-sectional view of the HPT disc (8) and its blade 12, with cold water flowing through the HPT disc (8) into (10) the turbine blade (12), through which the entire blades are joined from the top into the space in the U-shaped circle. Each end of the two ends of the U-ring is secured to the inside of the water-tight sealed bearing (R4, R5) to prevent water leakage. Since there is no weight on the bearings (R4, R5), there cannot be any speed loss of the rotational speed or stress over the HPT disc. Since the water cycle and cooling cycle are the same as the engine speed, the cooling is done using the cool air coming from the blades into the engine chassis, which provides a very good heat transfer, thus, the efficient cooling of the blades and discs are ensured.
INDUSTRIAL APPLICATION
The technical problems in the cooling process of the known Gas Turbine engines described above can be solved more successfully than the conventional techniques, with the External Gas Turbine water recirculation cooling technique. The invention is a product that can be produced in the industry using a design and manufacturing study in accordance with the invention. There is no complicated process in the manufacturing of the product and impeding the working order.

Claims

1- It is related to turbine cooling for gas turbine engines. The water recirculation pump (1) is equipped with a water recirculation pump (1) connected to the inlet of the main shaft (7) to deliver the required cooling water.
2 According to Claim 1, the invention is related to the turbine cooling for gas turbine engines; The inner shaft of the main shaft (7) is empty for the flow of water and the inlet portion of the main shaft (7) has 4 tabs (6) on the inside for the connection of the pump shaft (2).
3- According to the Claims 1 and 2, the invention is related to the turbine cooling for gas turbine engines; The outer part of the water recirculation pump chassis (3) is fixed to the outside of the engine protection casing (19) and to the inside of the water sealing bearing (Rl) which is secured in the horizontal funnel- shaped opening at the inlet of the main shaft (7) in the interior of the pump casing (3).
4 According to the Claims 1, 2 and 3, the invention is related to the turbine cooling for gas turbine engines; The interior of the motor main shaft (7) is of sufficient width to deliver sufficient cooling water to the turbine blades (12, 13).
5- According to the Claims 1, 2, 3 and 4, the invention is related to the turbine cooling for gas turbine engines; The end portion of the main shaft (7), the intermediate shaft (7, b) has 4 tabs (6) from the inside.
6- According to the Claims 1, 2, 3, 4 and 5, the invention is related to the turbine cooling for gas turbine engines; There are 4 U channels (5) on the inner shaft (7- b) 7 According to the Claims 1, 2, 3 , 4, 5 and 6, the invention is related to the turbine cooling for gas turbine engines; The inner shaft part (7-b) thickens in an arcuate manner to provide a better flow of water to the center of the LPT Disc.
8 According to the Claims 1, 2, 3, 4, 5, 6 and 7, the invention is related to the turbine cooling for gas turbine engines; The interior (10, 11) of the turbine disk (8, 9) is empty for the water flow, and each of the blades (12, 13) has channels for the flow of water.
9 According to the Claims 1, 2, 3, 4, 5, 6, 7 and 8, the invention is related to the turbine cooling for gas turbine engines; There is a water discharge apparatus (15, 16) around the turbine blades in a circular shape for the discharge of the hot water coming from the HPT and LPT blades, Inside the water discharge apparatus (15, 16), which is fixed to the left and right mounted bearings (R4, R5) from the outside, and the inside of the bearings (R4-R5) is fixed to each end of the U-rings, which connects the turbine blades (12, 13) from above.
10 According to the Claims 1, 2, 3, 4, 5, 6, 7, 8 and 9, the invention is related to the turbine cooling for gas turbine engines; There are water pipes (14) which serve as radiators to cool the hot water coming from the water discharge apparatus
(15.16), these pipes (radiators) (14) start from the water discharge apparatus
(15. 16) and are connected to the water channels in the engine chassis (19) near the air outlet of the LPC compressor (20), The water channels (19) in the engine chassis (19) are connected internally to the water circulation pump in the pump housing (3) and thus the water circulation is ensured.
PCT/TR2019/050543 2018-07-14 2019-07-08 Cooling of gas turbine engines with water recirculation WO2020018056A2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
TR2018/10053A TR201810053A2 (en) 2018-07-14 2018-07-14 COOLING GAS TURBINE ENGINES WITH WATER RECYCLING PUMP
TR2018/10053 2018-07-14

Publications (2)

Publication Number Publication Date
WO2020018056A2 true WO2020018056A2 (en) 2020-01-23
WO2020018056A3 WO2020018056A3 (en) 2020-06-11

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/TR2019/050543 WO2020018056A2 (en) 2018-07-14 2019-07-08 Cooling of gas turbine engines with water recirculation

Country Status (2)

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TR (1) TR201810053A2 (en)
WO (1) WO2020018056A2 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113669160A (en) * 2021-08-06 2021-11-19 西北工业大学 Turbine gas water spray cooling device

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2865598A (en) * 1954-03-03 1958-12-23 Merland L Moseson Air cooled turbine wheel design
GB0524266D0 (en) * 2005-11-29 2006-01-04 Lewis Stephen D The over clocked turbojet
TR201805946A2 (en) * 2018-04-27 2018-06-21 Uyanik Talat COOLING GAS TURBINE ENGINES WITH WATER RECYCLING PUMP

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113669160A (en) * 2021-08-06 2021-11-19 西北工业大学 Turbine gas water spray cooling device
CN113669160B (en) * 2021-08-06 2022-05-20 西北工业大学 Turbine gas water spray cooling device of underwater vehicle

Also Published As

Publication number Publication date
WO2020018056A3 (en) 2020-06-11
TR201810053A2 (en) 2018-08-27

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