Classifications

• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
  • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
  • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
  • F23R3/002—Wall structures
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
  • F05B2260/00—Function
  • F05B2260/20—Heat transfer, e.g. cooling
  • F05B2260/201—Heat transfer, e.g. cooling by impingement of a fluid
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
  • F05B2260/00—Function
  • F05B2260/20—Heat transfer, e.g. cooling
  • F05B2260/202—Heat transfer, e.g. cooling by film cooling
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
  • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
  • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
  • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies

Definitions

• GAS TURBINE ENGINE COMBUSTOR This invention relates to a gas turbine engine combustor and in particular to the construction of the wall of such a combustor.
• the wall is made up of two parts: a continuous outer wall and an inner wall made up of a number of partially overlapping inner wall elements.
• the outer wall and inner wall elements are maintained in spaced apart relationship and cooling air is directed through holes in the outer wall into the space defined between them.
• the cooling air flows through the space to be exhausted through gaps defined between the overlapping portions of the inner wall elements.
• the cooling air thereby provides convection cooling as it flows between the inner wall elements and outer wall and film cooling of the inner wall elements after it has been exhausted from the gaps between inner wall elements.
• a gas turbine engine combustor is provided with a wall structure which comprises an outer wall and an inner wall, said inner wall being constituted by a plurality of discreet wall elements, means being provided to maintain said wall elements and said outer wall in spaced apart relationship, said outer wall being apertured to permit the flow of cooling fluid into the spaced defined between said outer wall and said wall elements, each of said wall elements being apertured to facilitate the exhaustion of said cooling fluid from said spaces, means being provided to interconnect the periphery of each wall element and said outer wall said interconnection means defining a continuous wall around each wall element periphery so that a discreet chamber is thereby defined between each of said wall elements and said outer wall for the flow therethrough of said cooling fluid.
• Figure 1 is a sectional side view of the upper half of a ducted fan gas turbine engine which incorporates a combustor in accordance with the present invention
• Figure 2 is a sectional side view of a portion of the wall of the combustor of the gas turbine engine shown in figure 1;
• Figure 3 is a view on arrow A of figure 2;
• Figure 4 is a view on an enlarged scale of a portion of the combustor wall shown in figure 2;
• Figure 5 is a view on arrow B of figure 4.
• Figure 6 is a view similar to Figure 2 showing a modified form of combustor in accordance with the present invention.
• a ducted fan gas turbine engine generally indicated at 10 comprises, in axial flow series, an air intake 11, a propulsive fan 12, an intermediate pressure compressor 13, a high pressure compressor 14, combustion equipment 15, a high pressure turbine 16, an intermediate pressure turbine 17, a low pressure turbine 18 and an exhaust nozzle 19.
• the gas turbine engine 10 works in the conventional manner so that air entering the intake 11 is accelerated by the fan 12 to produce two air flows: a first air flow into the intermediate pressure compressor 13 and a second airflow which provides propulsive thrust.
• the intermediate pressure compressor 13 compresses the air flow directed into it before delivering that air to the high pressure compressor 14 where further compression takes place.
• the compressed air exhausted from the high pressure compressor 14 is directed into the combustion equipment 15 where it is mixed with fuel and the mixture combusted.
• the resultant hot combustion products then expand through, and thereby drive, the high, intermediate and low pressure turbines 16,17 and 18 before being exhausted through the nozzle 19 to provide additional propulsive thrust.
• the high, intermediate and low pressure turbines 16,17 and 18 respectively drive the high and intermediate pressure compressors 14 and 13 and the fan 12 by suitable interconnecting shafts.
• the combustion equipment 15 is constituted by an annular combustor 20 having radially inner and outer wall structures 21 and 22 respectively. Fuel is directed into the combustor 20 through a number of fuel nozzles (not shown) located at the upstream end 23 of the combustor 20. The fuel nozzles are circumferentially spaced around the engine 10 and serve to spray fuel into air derived from the high pressure compressor 14. The resultant fuel/air mixture is them combusted within the combustor 20.
• the radially outer wall structure 22 can be seen more clearly if reference is now made to figure 2. It will be appreciated, however, that the radially inner wall structure 21 is of the same general configuration as the radially outer wall structure 22.
• the radially outer wall structure 22 comprises an outer wall 24 and an inner wall 25.
• the inner wall 25 is made up of a plurality of discreet wall elements 26 which are all of the same general rectangular configuration and are positioned adjacent each other. The majority of each wall element 26 is arranged to 5 be equi-distant from the outer wall 24. . However, the periphery of each wall element 26 is provided with a continuous flange 27 to facilitate the spacing apart of the wall element 26 and the outer wall 24. It will be seen therefore that a chamber 28 is thereby defined between each 10 wall element 26 and the outer wall 24.
• Each wall element 26 is of cast construction and is provided with integral bolts 29 which facilitate its attachment to the outer wall 24.
• That air is then exhausted from the chambers 28 through a plurality of angled effusion holes 32 provided in each wall element 26.
• the effusion holes 32 are are so angled as to be aligned in a generally downstream C direction with regard to the general fluid flow through the combustor 20.
• each of the wall elements 26 is provided with two highly effective forms of cooling: impingement cooling and film cooling. They are therefore fully protected from the effects of the high temperatures within the combustor 20.
• a further feature of the present invention is that none of the wall elements 26 presents exposed edges to the combustion process within the combustor 20. Consequently the overheating problems which may be experienced with wall elements having such exposed edges are avoided.
• pedestals 33 are integral with the wall elements 26 and engage or terminate very close to the outer wall 24.
• the provision of the pedestals 33, which tend to be located in the central region of each wall element 26, results in a reduction in the number of the angled effusion holes 32 in each wall element 26. Consequently, the angled effusion holes 32 tend to be concentrated in the edge regions of the wall elements 26.

Landscapes

• Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Turbine Rotor Nozzle Sealing (AREA)

Priority Applications (3)

Applications Claiming Priority (2)

Publications (1)

Family

ID=10692006

Family Applications (1)

Country Status (5)

Cited By (17)

Families Citing this family (4)

Citations (7)

• 1991
  • 1991-03-22 GB GB919106085A patent/GB9106085D0/en active Pending
• 1992
  • 1992-02-03 DE DE69204280T patent/DE69204280T2/de not_active Expired - Lifetime
  • 1992-02-03 EP EP92904247A patent/EP0576435B1/de not_active Expired - Lifetime
  • 1992-02-03 WO PCT/GB1992/000201 patent/WO1992016798A1/en active IP Right Grant
  • 1992-02-03 JP JP4504028A patent/JPH06507468A/ja active Pending

Patent Citations (7)

Also Published As

Similar Documents

Legal Events