DE2133256A1 - Combustion part of gas turbines - Google Patents

Description

DAD HT AIT-VTA LI WOODB DIPIi. ING. ! B. SBUBQ 89 ACQ uEK-iTiuinu wmjsranc-w «] κ, ns *

W. 539

Augsburg, June 30, 1971

Westinghouse Electric Corporation, Westinghouse Building, Gateway Center, Pittsburgh, Allegheny County, Pennsylvania 15 222, V.St.A.

Combustion 11 of gas turbines

The invention relates to the combustion part of gas turbines, which is housed in a housing, in Cross-section circular and divided into two halves and a plurality of annular within the housing

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arranged combustion chambers, wherein an annular end wall of the housing with an annular arrangement of openings for supplying the combustion chambers with fuel is provided.

As the output of gas turbines increases, so does the size of the Gas turbines accordingly. In the known turbine designs, the combustion part has the largest Housing diameter. As the diameter of the combustion casing increases, its wall thickness also increases and more material is required for the housing to withstands additional stresses acting on the housing walls. For machining the housing are In addition, larger machines are required and there are higher freight costs. After all, the buildings are in what the turbines are housed larger and more expensive.

The outside diameter of the combustion case is determined by the size of the combustion chambers and the distance between the individual combustion chambers and the number of combustion chambers that are used to deliver the hot gas to drive the Turbine impeller are required. When the desired force to drive the turbine runner has been determined, the size, the distance and the number of combustion chambers are selected.

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Presently the distance between each other becomes eils neighboring Combustion chambers are only determined after the size and number of the combustion chambers have been selected because each combustion chamber is too It must be removable for maintenance purposes through a round opening in the end wall of the combustion chamber housing. The diameter these end wall openings is each slightly larger than the largest outer diameter of the combustion chambers. Locking plates each have an even larger diameter than the end wall openings so that they are connected to the end wall can be screwed. In addition, the distance j

between adjacent closure plates determined by the distance, which the near horizontal Have flapping arranged closure plates of these flanges. Because each combustion chamber has its own front wall opening with a closure plate of a correspondingly large diameter at a certain distance from the horizontal flanges has, only a very limited reduction in the diameter of the combustion housing is possible.

The invention aims to solve the problem, ™

to design the combustion part of gas turbines in such a way that the combustion chamber arrangement has a substantially smaller Has overall diameter than known combustion chamber arrangements and yet can be easily installed, monitored and removed for maintenance.

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In order to achieve this object, the invention includes a combustion part of gas turbines, which housed in a housing, circular in cross section and divided in half and a plurality of has combustion chambers arranged in a ring within the housing, wherein an annular end wall of the housing is provided with an annular arrangement of openings for supplying the combustion chambers with fuel. Such a Combustion part is characterized according to the invention in that the combustion chambers are each close to one another are arranged and that the diameter of at least every second opening of the openings formed in the end wall is smaller than the largest outer diameter of the respectively assigned combustion chamber.

Several embodiments of the invention are shown in the drawings and will be described in more detail below described. Show it:

Fig. 1 partially in longitudinal section a

Gas turbine, in which part of the combustion casing is removed, so that according to the Invention arranged combustion chambers are visible,

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FIg. 2 shows a section along the

Line H-II in Fig. 1,

3 shows an enlarged scale

Section along the line HI-III in Fig. 1,

Fig. 4 is a view from the right of the

in Fig. 3 illustrated arrangement,, f

5 shows another embodiment

of the combustion part according to the invention in the same sectional view as in Fig. 3,

Fig. Β still another embodiment

shape of the combustion part

according to the invention in the same λ

Section view as in Fig. 3,

Fig. 7 again a further Aus

management form of the combustion part according to the invention in the same sectional view as

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In Flg. 2,

Pig. 8 as an enlarged detail

those in Pig. 7 near the horizontal splash arranged combustion chambers,

9 shows another embodiment

of the combustion part of the invention in the same sectional view as in Fig. 8, and

Fig. 10 shows another one

Embodiment of the combustion part according to the invention in the same Sectional view as in FIG. 8.

In Fig. 1, the combustion part 10 is an axial turbine system shown. As the combustion part is used in every suitable type of gas turbine system can find, only the part of the turbine system is shown, which is necessary for understanding the invention. the

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Turbine system has an axial air compressor 12 for introducing air into the combustion part 10 as well as a standing in flow connection with the combustion part 10 and hot combustion products therefrom receiving gas turbine 14 for powering the turbine system.

The air compressor 12 has, in a known manner, a multi-stage impeller arrangement 15 (FIGS. 2 and 3) with rotor blades 16, which cooperate with guide vanes 17 (Pig. I and 2) in such a way that the air guided through |

for the combustion part 10 is compressed. The on Air escaping from the compressor 12 is introduced into a storage space which is formed by a housing arrangement 19 is.

The housing assembly 19 is along a central Horizontal plane divided into upper and lower semi-cylindrical housing halves 20 and 21, which are coaxial with the Central axis of the turbine system are arranged. A front hood-shaped end wall 22 is with its downstream located end attached to the outer casing of the compressor 12 and with its upstream end along vertically extending annular flanges 22a and 22b with the aid of fastening means 22c on the housing halves 20 and 21 attached. A downstream one

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annular end wall 23 is with its downstream located end on the outer casing of the turbine 14 and with its upstream end longitudinally vertical

extending planes 22a and 22b with the aid of fastening means 22c on the housing halves 20 and 21 attached.

The turbine 14 is an axial turbine and has a A plurality of expansion stages, which are formed by a plurality of rows of guide vanes 24 with an equal plurality of on a turbine runner 26 attached blades cooperate. The turbine runner 26 is via known devices, not shown drivingly connected to the compressor impeller 15.

As shown in Pig. 2 is within the housing 19 a plurality of a distance from each other and each having the same distance from the center line of the turbine system and belonging to the canister type Combustion chambers 30 assigned. The combustion chambers 30 each also have the same spacing within the housing 19 from each other and their axes are essentially parallel to the longitudinal center line of the turbine system and the Housing assembly 19.

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Since the combustion chambers 30 are essentially identical, only one will be described below. The combustion chamber 30 belongs to the Stuferibüchsenbauart and has upstream of an end portion 31 made up of a plurality of cylindrical sleeves 32 of each stepped size which slightly overlap each other and form a primary combustion zone 33. The cans 32 each have an annular arrangement of openings which introduce primary air into the combustion zone 33, the combustion of the upstream end via fuel supply devices (not shown) injected fuel carries.

each combustion chamber 30 also has a central cylindrical portion 41 with a plurality of annular Rows of openings 42 are provided which allow secondary air to enter the combustion chamber during operation. In addition, the combustion chamber 30 faces downstream located end a transition part 44 on «its cylindrical Front part 45 slightly overlapping the cylinder I Rischen part 41 encloses and its rear tubular part 46 progressively in the contour of the circular Cross section at the connection point with the cylindrical part 41 to a ring segment-shaped cross section at its outlet end part 48 changes. the

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The arc length of the ring segment at the outlet 48 is chosen such that it is together with the outlets of the other combustion chambers 30 a complete annulus which forms the hot products of combustion from the combustion chambers 30 into the blades 24 and 25 of the turbine 14 initiates and thereby the turbine 14 on the drive gases the entire scope supplies what is known per se and can best be seen from FIGS. The diameter each end wall opening 35 is smaller than the largest diameter of the associated combustion chamber 30, which is on cylindrical part 41 of the combustion chamber in question occurs.

In the embodiment of the invention shown in FIGS. 1 and 2, the upstream end wall 22 is of the combustion part 10 with a multiplicity of circular openings 35 arranged at a mutual distance provided, which each have the same distance from the longitudinal center line of the turbine system and which each have one Combustion chamber is assigned. Each end wall opening 35 takes a fuel supply device known per se, not shown which feeds fuel to each combustion chamber 30 and closes the openings 35. A frustoconical hood part 39 closes the outermost front end of the combustion chamber 30 and is used for Adaptation to the fuel supply, not shown

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furnishings. The hood portion 39 acts with the nozzle in this way together that there is no air in the combustion zone 33 can flow in. In addition, ignition devices are not shown for igniting the fuel-air mixture provided in the combustion zone 33.

According to the illustration in FIG. 3, each opening 35 is incorporated into a ring attachment 57, which is also visible in FIG. 1. The extension 57 in the vicinity of an upper horizontal flange 50 and the extension in the vicinity of a lower horizontal flange 51 each have a certain distance from the flange in question for the same reasons as the closure plates for the end wall openings in known turbine designs. A fuel supply device (not shown) is inserted through each end wall opening 35 and supplies the combustion chamber with fuel. Since the required with the known turbine designs closure plates at the combustion part of the invention are not present, a can the threshold distance S _n, equal to the distance between adjacent combustion chambers 30 is to be chosen in a suitable manner and therefore, the bundle assembly of the combustion chambers 30 can be more compact are executed. The approach 57 can be moved sufficiently close to the upper surface of the horizontal flange 50 so that

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the largest diameter of the combustion chamber 30, which is equal to the diameter of the cylindrical part 41, see FIGS. 3 and 4, projects into the horizontal area which is defined by the upper surface and by the lower surface of the upper horizontal flange 50. With a suitably selected distance S _ß between the combustion chambers 30, the largest diameter of the combustion chamber in the vicinity of the upper horizontal flange 50 extends into an area which is defined by the upper and lower surfaces of the upper horizontal flange 50. The largest diameter of the combustion chamber in the vicinity of the lower horizontal flange 51 extends into a horizontal area which is defined by the lower and upper surfaces of the lower horizontal flange 51.

This results in a considerable reduction in the overall diameter of the housing arrangement I9 of the combustion part 10. This overall diameter D ™ is calculated as follows t

^D T - ^D CL ^{+ D} C ^{+ 2} < ^S 1 ^{+ S} 2 ^C CL * * ^D CL- ^N C < ^D C ^{+ S} c) ^D CL - M ⁰ C ^{+ 8} C>'* *

^D T -. ■ + ^D

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where:

Du = total diameter of the housing, Ώ _ητ = diameter of the circle on which the central

points of the combustion chambers of the BrennkamtnerbUndels lie,

Dr. ^β largest diameter of the combustion chamber, S, * distance between the combustion chamber and the

Casing,

S ₂ - Dioke of the housing,
S, = width of the horizontal flange, C _CL »circumference of the center circle of the combustion chamber,

N _c * number of combustion chambers, and S _c ■ distance between adjacent combustion chambers.

The reduction in diameter with respect to a

Diameter D. of the housing of a known turbine con-A

The structure and the diameter Dm of the housing of a combustion part can be achieved according to the invention, depends on the distance Sq that is selected between adjacent combustion chambers. In table Σ, on the basis of the equations given above, for different distances S ~ between neighboring combustion chambers together with

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/ 1OMI4 / 1107 ₄ ORDINAL INSPECTED

the housing outside diameter D. of a known combustion * partly the actually resulting reduction of the diameter is given:

Tabel I. (D -D) / mm S _c / mm D / mm D./mra
Ä 1575 50.8 2794 4369 1449 76.2 2920 4369 1321 101.6 3048 4369 1194 127.0 3175 4369 IO67 152.4 3302 4369 813 203.2 3556 4369

In a typical calculation example from Table I, in which the distance S _c between adjacent combustion chambers is 203.2 mm, the number of combustion chambers N "is 16, the largest diameter D _{r of} each combustion chamber is 304.8 mm, the distance S between of the combustion chamber and the vertical flange is 152.4 mm, the thickness of the housing Sg is 50.8 mm and the thickness of the vertical flange S is 140 mm, the total diameter Drj-, according to the equations given above, is approximately

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3556 mm. If D _{T is} subtracted from the overall diameter D _A of 4569 mm, the result is a reduction in the diameter of the combustion casing by 813 mm.

In order to be able to remove the combustion chambers 30 from the housing arrangement 19, the upper cylindrical Housing half 20 can be removed. The burners can, however, without removing the upper cylindrical housing half 20 inspected through the end wall openings 35 hinduoh after the fuel supply device has been removed.

Another embodiment of the combustion part according to the invention, the combustion chamber bundle arrangement of which is similar to that shown in FIGS. 1, 2, 3 and 4 and in FIG is shown, differs from this by the following features: At mutual distance from each other arranged combustion chambers 65 are around the central axis of the Turbine around and at the same distance from this I.

arranged. The housing arrangement of the combustion part is divided into upper and lower semi-cylindrical housing halves 66 and 6j in each case along a central horizontal plane. The housing halves 66 and 67 have horizontally projecting flanges 68 and 69 which are connected to one another by fastening means (not shown). One upstream

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located end wall 71, which is part of the housing assembly forms, has an annular arrangement of openings 72 each having the same distance from one another, which are each assigned to a combustion chamber 65. The openings 72 are each incorporated as bores in an annular projection 73. The combustion chambers 65 nearby the horizontal planes 68 and 69 are arranged in such a way that none of them extend into the horizontal area defined by the splash. This embodiment the combustion part according to the invention is not as compact as the previously described embodiment, However, it has the additional advantage that a greater distance between the lugs 73 and the paddles 68 and is possible.

Another embodiment of the combustion part according to the invention is shown in FIG. 6 and differs differs from the embodiments of the invention described above in the following ways: A plurality of combustion chambers 761 those spaced from each other and from the Central axis of the turbine are arranged, is enclosed by a turbine housing arrangement. The housing arrangement is divided into upper and lower semi-cylindrical halves attached to their horizontal planes 78 and 79

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ORfGfNAL, INSPECTED

are connected to one another by fastening means not shown. A plurality of annular lugs 81 are spaced from one another and from the central axis of the turbine, one lug corresponding to each combustion chamber 76. One of the combustion chambers 76 in the vicinity of a horizontal flange, namely the combustion chamber located in the vicinity of the upper horizontal flange 78 as shown in FIG. 6, extends with its part having the largest diameter into both the upper and lower housing halves . * In this combustor bundle arrangement, the combustors 76 need to be near the horizontal flanges 78 and not equidistant from the horizontal flanges. This results in additional construction space and an asymmetrical bundle arrangement is possible.

7 and 8 is yet another embodiment the combustion chamber bundle arrangement according to the

Invention shown. The combustion part of a gas *

turbine has a housing assembly 83 that from an upper cylindrical housing half 84 and a lower cylindrical housing half 85, which on horizontal flanges 87 and 88 by not shown

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10 * 314/1197

Fastening means are interconnected. An upstream, plate-shaped end wall 90 is longitudinal vertically protruding flanges 91 by not shown Fasteners attached to the upper and lower housing halves. A plurality of combustion chambers 92, which are arranged at the same distance from each other and at the same distance from the central axis of the turbine, is arranged in a ring inside the combustion housing. A corresponding multiplicity of openings 9 ^ is formed within annular lugs 95 corresponding to combustion chambers 92.

Lugs with two different diameters are alternately attached to the end wall 90. The first or smaller extension 95a defines the openings 9k for receiving the fuel supply device, not shown, via which fuel is supplied to the combustion chambers. The extension 95a has a diameter which is smaller than the largest diameter of the combustion chamber 92, see FIG. 8. The second or larger extension 95b receives a closure plate 97 which closes a circular opening 98 formed in the end wall 90, whose diameter is slightly larger than the diameter of the combustion chamber 92. In the closure plate 97 there is an opening 9 ^ concentrically to the

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Ji

Receiving the fuel supply device for the combustion chamber 92 is arranged. This part of the incineration assembly essentially resembles an arrangement already known in printed literature.

As shown in Fig. 8, the closure plate 97 is in the upper housing half 84 in the vicinity of the upper horizontal flange 87 and arranged at a certain distance from this. That of the locking plate The associated combustion chamber 92 is introduced through the opening 98 provided with the large diameter .bzw. taken out. For the combustion chamber 92 near the The lower horizontal flange 88 does not have a large opening formed in the end wall 90 for removal Diameter available. For this reason, this combustion chamber 92 can be closer to within the housing arrangement horizontal flange 88 to be arranged because the extension 95a has a much smaller diameter than the locking plate. The combustion chamber 92 in the vicinity of the lower horizontal flange 88 protrudes into a horizontal | zontal area, which is defined by the lower horizontal flange 88.

In this embodiment of the combustion part according to According to the invention, the combustion chamber 92 is removed

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without an associated closure plate, through a large diameter opening 98 formed in the end wall 90 near the combustion chamber _: after the adjacent combustion chamber has been removed. "This alternating removal of the combustion chambers in this bundle arrangement is somewhat easier than the removal of the upper housing half described above, although under certain conditions the overall diameter of the housing arrangement 83 compared to the previously described embodiment is somewhat larger.

It will be noted, however, that fewer or more closure plates as shown in Fig. 7, and that the closure plates on both sides of the horizontal flange can be arranged. In addition, there are many combinations within the scope of the invention of large and small openings 98 and 94 possible.

Another embodiment of that shown in Figs The bundle arrangement shown, in which the combustion chambers are alternately removed, is shown in FIG. A plurality of combustion chambers 101 is housed in an annular manner within a combustion housing arrangement 102. The housing assembly 102 consists of upper and lower semi-cylindrical housing halves 103, 104 on which

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upstream an end wall 105 is attached, which along a vertically projecting flange 106 by not shown Fastening means on the housing halves 105 and 104 is attached. The upper and lower semi-cylindrical housing halves 103 and 104 are more horizontally protruding longitudinally Plane 108 and 109 connected to one another by fastening means (not shown). The combustion chamber 101, the is arranged in the vicinity of the upper horizontal flange 108, can by one in the end wall 105 with a slightly larger Opening 110 formed in diameter can be inserted or removed, which is closed by a closure plate 111 is. The combustion chamber 101 in the vicinity of the lower horizontal flange 109 has a corresponding opening 110 for insertion or removal and must therefore by one on one side or the other adjacent Opening 110 can be inserted or removed therethrough.

According to the illustration in FIG. 9, the combustion chamber 101 is at a distance therefrom in the vicinity of the lower horizontal flange. This results in an i

slightly larger clearance for the combustion chambers arranged in the vicinity of the horizontal flanges 108 and 109 than in the embodiment of the combustion part according to the invention shown in FIG. 7.

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Yet another embodiment of that shown in FIG. 7 illustrated bundle arrangement according to the invention is shown in FIG. A variety of combustion chambers is annular within a combustion canister 116 The housing 116 is divided into upper and lower semi-cylindrical halves 117 and 118, the are connected to one another along horizontal flanges 120 and 121 by suitable fastening means. To the Housing halves 117 and 118 are fastened along vertical flanges upstream of an end wall 119. The combustion chamber is arranged in the upper housing half 117 so close to the upper horizontal flange 120 that you largest diameter in the area defined by the horizontal flanges 12 and 121 and also in both the upper housing half 117 as well as into the lower housing half 118 protrudes.

The combustion chamber 115 located in the vicinity of the lower horizontal flange is spaced from the lower horizontal flange and is through a larger diameter opening 12 ^ therethrough inserted or removed, which is formed in the end wall 119. The opening 123 is through a closure plate 124 sealed.

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The combustion chambers 115, which are located in the vicinity of the combustion chamber provided with the verso plate 124, are removable through the opening provided with the larger diameter.

The main advantage of this embodiment of the combustion part according to the invention is that a more compact bundle arrangement than that shown in FIG Embodiment can be provided because the Combustion chamber in both the upper and the lower "

Housing half can be arranged and lies in a horizontal plane through the two horizontal Splash is set.

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Claims (4)

ZH Claims; Combustion part of gas turbines, which is housed in a housing, circular in cross section and in is divided into two halves and has a plurality of combustion chambers arranged in a ring within the housing, wherein an annular end wall of the housing with an annular array of openings for supplying the Combustion chambers are provided with fuel, characterized in that the combustion chambers (92; 101; 115) are each narrow are arranged side by side, and that the diameter of at least every second opening (94) in the end wall (90; 105) formed openings (94, 98; 110; 12J) is smaller than the largest outer diameter of each assigned combustion chamber. · 2. Turbine according to claim 1, characterized in that at least one of the combustion chambers (92; 115) to extends into an area which is enclosed by splashes (87, 88; 120, 121) which fit one another and protruding parallel to the turbine center axis in the vicinity of a longitudinal sectional plane passing through the turbine center axis are formed on the housing halves (84, 85; 116, II7). - 24 109884/1197 3. Turbine according to claim 1 or 2, characterized in that the combustion chambers (92; 101; 115) arranged in the vicinity of the openings (94) provided with the smaller diameter are each provided with the larger diameter openings (98; 110; 123) can be removed through the housing (8j5; 102; II6) when the combustion chambers associated with the openings provided with the larger diameter are removed. 4. Turbine according to claim 1 or 2, characterized in that the diameter of the openings (35; 72) formed in the end wall (22; 71) is in each case smaller than the outer diameter of the combustion chambers (30; 65 ϊ 7δ) ηηύ that the combustion chambers Can be removed from the housing (IQ) when one of the housing halves (20, 21; 66, 67) is removed. - 25 109884/1197