CN115506919A - Lightweight solid rocket engine composite construction spray tube device - Google Patents

Lightweight solid rocket engine composite construction spray tube device Download PDF

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Publication number
CN115506919A
CN115506919A CN202210549573.4A CN202210549573A CN115506919A CN 115506919 A CN115506919 A CN 115506919A CN 202210549573 A CN202210549573 A CN 202210549573A CN 115506919 A CN115506919 A CN 115506919A
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CN
China
Prior art keywords
shell
section
resistant layer
ablation
throat
Prior art date
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Pending
Application number
CN202210549573.4A
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Chinese (zh)
Inventor
杜伊杨
李靖
杨晓红
马虎
夏镇娟
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Nanjing University of Science and Technology
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Nanjing University of Science and Technology
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Publication date
Application filed by Nanjing University of Science and Technology filed Critical Nanjing University of Science and Technology
Priority to CN202210549573.4A priority Critical patent/CN115506919A/en
Publication of CN115506919A publication Critical patent/CN115506919A/en
Pending legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/97—Rocket nozzles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B1/00—Layered products having a non-planar shape
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/04—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • B32B15/08—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material of synthetic resin
    • B32B15/098—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material of synthetic resin comprising condensation resins of aldehydes, e.g. with phenols, ureas or melamines
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/14—Layered products comprising a layer of metal next to a fibrous or filamentary layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B27/00—Layered products comprising a layer of synthetic resin
    • B32B27/06—Layered products comprising a layer of synthetic resin as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B27/00—Layered products comprising a layer of synthetic resin
    • B32B27/42—Layered products comprising a layer of synthetic resin comprising condensation resins of aldehydes, e.g. with phenols, ureas or melamines
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
    • B32B3/10—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material
    • B32B3/14—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material characterised by a face layer formed of separate pieces of material which are juxtaposed side-by-side
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
    • B32B3/10—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material
    • B32B3/18—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material characterised by an internal layer formed of separate pieces of material which are juxtaposed side-by-side
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B33/00—Layered products characterised by particular properties or particular surface features, e.g. particular surface coatings; Layered products designed for particular purposes not covered by another single class
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/97—Rocket nozzles
    • F02K9/974—Nozzle- linings; Ablative coatings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/10—Inorganic fibres
    • B32B2262/106—Carbon fibres, e.g. graphite fibres
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/30—Properties of the layers or laminate having particular thermal properties
    • B32B2307/304—Insulating
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/70—Other properties
    • B32B2307/714—Inert, i.e. inert to chemical degradation, corrosion

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)

Abstract

The invention discloses a lightweight composite structure nozzle device of a solid rocket engine, which comprises: a convergence section ablation-resistant layer, a convergence section heat-insulating layer, a throat insert back wall, an expansion section ablation-resistant layer, an expansion section heat-insulating layer, a shell and a set screw. In order to reduce the quality of the shell, the expansion section of the spray pipe shell is partially hollowed, the hollowed shape is isosceles trapezoid, and the hollowed part extends into the shell to a certain depth without damaging the molded surface of the inner wall surface of the shell; by uniformly driving the set screws in the circumferential direction of the expansion section part of the shell and carrying out local inclined plane design on the inner wall surface of the back wall of the throat liner, the risk that the erosion resistant layer of the throat liner and the expansion section is blown off by gas is effectively reduced; the inner surface of the cylindrical section of the shell is provided with a boss protruding inwards and used for axially limiting the back wall of the throat liner, sharing a part of axial load and improving the structural reliability of the engine during working.

Description

Lightweight solid rocket engine composite construction spray tube device
Technical Field
The invention belongs to the technical field of engines, and particularly relates to a composite structure spray pipe device of a lightweight solid rocket engine.
Background
For the spray pipe, when the working time is long and the propellant is high-energy propellant containing metal powder, such as modified double-base propellant and composite propellant, the spray pipe structure needs to adopt a composite structure spray pipe. The composite structure spray pipe is generally designed in a multilayer mode, the typical structure of the composite structure spray pipe is a three-layer structure comprising an ablation-resistant layer, a heat insulation layer and a shell, the ablation-resistant layer mainly plays a role in resisting high-speed gas scouring, the heat insulation layer mainly plays a role in reducing heat transfer to the shell, and the shell plays a role in structural support.
In the composite structure nozzle, the shell mass fraction is large. For composite nozzle, the shell material is usually selected from metal materials, such as high-strength steel, high-strength aluminum alloy, titanium alloy, and the like. Wherein, the high-strength steel material has too high density, which can cause the overall quality of the spray pipe to be increased; the strength of the titanium alloy is high, but the material cost is too high; the high-strength aluminum alloy has low density, but the material performance of the high-strength aluminum alloy is too sensitive to temperature change, and the strength of the aluminum alloy is obviously reduced along with the increase of the temperature. Under the reliable condition of assurance nozzle shell intensity, for the consideration of cost and structural quality, select more and use high strength aluminum alloy as the shell material, can reduce the influence of temperature to its intensity through the rational design of structure. In design, the designed shell usually has little change in thickness along the axial direction of the nozzle based on design simplification principle and material easy-to-machine forming principle, but actually, the design often results in larger mass of the nozzle shell, and the nozzle shell expansion section also has space for further weight reduction.
Disclosure of Invention
The invention aims to provide a composite structure spray pipe device of a lightweight solid rocket engine, which is characterized in that the expansion section part of a spray pipe shell is partially hollowed to reduce the weight while the reliability of the spray pipe structure is ensured, so that the lightweight design of the spray pipe is realized.
The technical solution for realizing the purpose of the invention is as follows:
a lightweight composite structure spray pipe device of a solid rocket engine comprises a shell, a spray pipe heat insulation layer structure and an ablation-resistant layer structure, wherein the spray pipe heat insulation layer structure and the ablation-resistant layer structure are arranged in the shell;
the tail ends of the spray pipe heat insulation layer structure and the ablation resistant layer structure exceed the shell, and the shell does not completely cover the spray pipe heat insulation layer structure and the ablation resistant layer structure;
the casing afterbody circumference spaced is equipped with a plurality of hollow out construction, and hollow out construction is the blind hole and is trapezoidal, and trapezoidal upper base displacement front end, trapezoidal lower base are located the rear end.
Compared with the prior art, the invention has the remarkable advantages that:
(1) The shell expansion section is partially hollowed, the shell does not completely cover the spray pipe heat insulation layer structure and the ablation-resistant layer structure, the hollowed shape is isosceles trapezoid, the hollowed volume is gradually increased along with the gradual approach of the tail end of the shell in the axial direction of the spray pipe, the hollowed treatment only penetrates into the shell to a certain depth (blind hole), the integrity of the inner wall surface of the shell is ensured, the strength of the shell can be effectively maintained, the complete profile contact between the shell and the ablation-resistant layer can be ensured, and the bonding strength between the shell and the ablation-resistant layer can be further effectively ensured.
(2) The back wall of the throat liner is provided with the inclined plane, the circumferential direction of the shell is uniformly provided with the set screws, and the middle cylindrical section of the shell is provided with the inward boss, so that the structure reliability is ensured, and the structure is simplified.
(3) The invention has no excessive step design on the heat insulation layer and the ablation resistant layer, and has reasonable processing and high assembly.
Drawings
FIG. 1 is a schematic view of a composite nozzle of the present invention.
FIG. 2 is a schematic view of a composite structural nozzle shell of the present invention.
Detailed Description
The invention is further described with reference to the following figures and embodiments.
The schematic diagram of the composite structure spray pipe of the embodiment is shown in fig. 1, and comprises a shell 1, wherein the front end of the shell 1 is a convergent section, the middle of the shell is a cylindrical section, and the rear end of the shell is an expansion section, a convergent section heat insulation layer 2, a throat lining back wall 4 and an expansion section heat insulation layer 6 are sequentially arranged in the convergent section, the cylindrical section and the expansion section, and the convergent section heat insulation layer 2, the throat lining back wall 4 and the expansion section heat insulation layer 6 form a spray pipe heat insulation layer structure. The convergent section heat-insulating layer 2, the throat lining back wall 4 and the expansion section heat-insulating layer 6 are sequentially internally provided with a convergent section ablation-resistant layer 3, a throat lining 5 and an expansion section ablation-resistant layer 7, and the convergent section ablation-resistant layer 3, the throat lining 5 and the expansion section ablation-resistant layer 7 form an ablation-resistant layer structure. The ablation- resistant layers 2 and 6 of the convergence section and the expansion section are made of carbon cloth/phenolic aldehyde materials, the throat liner 4 is made of carbon/carbon composite materials, the heat insulation layer is made of high silica/phenolic aldehyde materials, and the shell 1 is made of high-strength metal materials.
The tail ends of the spray pipe heat insulation layer structure and the ablation resistant layer structure exceed the shell 1, and the shell 1 does not completely cover the spray pipe heat insulation layer structure and the ablation resistant layer structure; the tail of the shell 1 is circumferentially provided with a plurality of hollow structures 9 at intervals, each hollow structure is a blind hole and is trapezoidal, the upper bottom of each trapezoid is located at the front end, and the lower bottom of each trapezoid is located at the rear end along the airflow direction. The multiple columns of hollow structures are arranged at equal intervals along the circumferential direction of the tail of the shell, and each column of hollow structures is provided with a plurality of isosceles trapezoid hollow structures.
FIG. 2 is a schematic diagram of a casing, and is used for performing local hollow treatment on an expansion section part of the casing of the spray pipe, wherein the hollow shape is isosceles trapezoid, and in the axial direction of the spray pipe, along with the gradual approach to the tail end of the casing, the hollow volume is gradually increased, and the hollows are uniformly arranged in the circumferential direction. The fretwork is handled and only goes deep into the certain degree of depth (blind hole) of casing, has guaranteed the integrality of casing inner wall face, can effectively keep casing intensity, can guarantee again that casing and resistant ablation layer have complete profile contact, further effectively guarantees the bonding strength between casing and resistant ablation layer.
The shell 1 is provided with an inward boss 11 at the tail part of the middle cylindrical section, so that effective axial support can be provided for the back wall 4 of the throat liner; the inner surface of the back wall 4 of the throat insert is provided with an inclined surface 41 which is inclined inwards from front to back, so that effective axial support can be provided for the throat insert 5; eight set screws 8 are arranged on the expansion section of the shell along the circumferential direction, and the screws 8 penetrate through the shell 1 and the expansion section heat insulation layer 6 and penetrate into the expansion section ablation-resistant layer 7 to a certain depth so as to prevent the expansion section ablation-resistant layer 7 from being blown off by fuel gas in the working process of the engine.
One side of the convergent section is in a gas incoming flow direction, incoming flow gas flows at subsonic speed, the gas expands and accelerates when flowing through the convergent section, reaches the sonic speed near the throat position, and then continues to expand and accelerate in the divergent section, so that the gas is converted from subsonic speed to supersonic speed. The inner wall surface of the ablation resistant layer of the nozzle needs to bear the scouring of high-speed gas, so that a large axial force is borne in the axial direction. In the long-time working process of the engine, the nozzle ablation-resistant layer is heated seriously, so that the local binder is pyrolyzed, the material interface is in a nonlinear contact state, and the main acting force direction of the nozzle thermal-insulation layer on the nozzle ablation-resistant layer is normal along the material interface, so that the 5-throat liner can be effectively prevented from being blown off by gas when the interface is debonded by carrying out inclined surface design on the inner wall surface of the throat liner back wall 4, and the reasonability of assembly is ensured; by driving 8-set screws into the shell, the expansion section ablation-resistant layer 7 can be effectively prevented from being blown off by gas when the interface is debonded; the inner surface of the cylindrical section of the shell is provided with a boss 11 protruding inwards, and the boss 11 is used for axially limiting the back wall of the throat liner, sharing a part of axial load and improving the structural reliability of the engine during working.
In the gas flowing process, along with the continuous increase of the gas flow rate, the gas static pressure and the static temperature are both continuously reduced, so that the pressure load and the heat load borne by the expansion section structure of the spray pipe are both reduced compared with the positions of the convergence section and the throat part of the spray pipe. Fig. 2 is a schematic view of a composite structure spray pipe shell, wherein the expansion section of the spray pipe shell is partially hollowed, and the hollowed shape is an isosceles trapezoid. The hollows are uniformly arranged in the circumferential direction of the spray pipe; in the spray tube axis direction, along with being close to the casing tail end gradually, the fretwork volume increases gradually. The fretwork is processed and only deepened into certain degree of depth (non-through hole) of casing, has guaranteed the integrality of casing inner wall, can effectively keep casing intensity, can guarantee again that casing and resistant ablation layer have complete profile contact, further effectively guarantee the bonding strength between casing and resistant ablation layer. The complexity of the molded surface of the shell is increased by the hollow-out processing, so that the conventional shell processing mode is not applicable, and the shell material can be molded by means of a 3D printing technology.

Claims (7)

1. A lightweight solid rocket engine composite structure spray pipe device comprises a shell, a spray pipe heat insulation layer structure and an ablation-resistant layer structure, wherein the spray pipe heat insulation layer structure and the ablation-resistant layer structure are arranged in the shell; it is characterized in that the preparation method is characterized in that,
the tail ends of the spray pipe heat insulation layer structure and the ablation resistant layer structure exceed the shell, and the shell does not completely cover the spray pipe heat insulation layer structure and the ablation resistant layer structure;
the casing afterbody circumference spaced is equipped with a plurality of hollow out construction, and hollow out construction is the blind hole and is trapezoidal, and trapezoidal upper base displacement front end, trapezoidal lower base are located the rear end.
2. The composite nozzle assembly of a lightweight solid rocket engine according to claim 1, wherein said housing has a converging section at the front end, a cylindrical section in the middle, and an expanding section at the rear end, and wherein a converging section thermal insulation layer, a throat lining back wall, and an expanding section thermal insulation layer are sequentially disposed in said converging section, cylindrical section, and expanding section, and said converging section ablation-resistant layer, throat lining back wall, and expanding section thermal insulation layer constitute the nozzle thermal insulation layer structure.
3. The composite structure nozzle device of a lightweight solid rocket engine according to claim 2, wherein said heat insulating layer of the convergent section, the throat liner back wall and the heat insulating layer of the divergent section are provided with an ablation resistant layer of the convergent section, a throat liner and an ablation resistant layer of the divergent section in sequence, and the ablation resistant layer of the convergent section, the throat liner and the ablation resistant layer of the divergent section constitute an ablation resistant layer structure.
4. The composite structure nozzle arrangement of a lightweight solid rocket engine according to claim 3 wherein the throat insert backing wall inner surface is beveled inward from front to back for providing axial support to the throat insert.
5. The composite structure nozzle assembly of a lightweight solid rocket engine according to claim 3 wherein the cylindrical section aft portion is provided with inward projections for providing axial support to the throat insert back wall.
6. The composite structure nozzle assembly of a lightweight solid rocket engine according to claim 3 wherein said expansion segments are provided with screws that extend through the housing and the expansion segment insulation layer and into the expansion segment ablation resistant layer.
7. The composite structure nozzle device of a lightweight solid rocket engine according to claim 1, wherein multiple rows of hollow structures are arranged at equal intervals along the circumference of the tail of the housing, and each row of hollow structures is provided with multiple isosceles trapezoid hollow structures.
CN202210549573.4A 2022-05-20 2022-05-20 Lightweight solid rocket engine composite construction spray tube device Pending CN115506919A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202210549573.4A CN115506919A (en) 2022-05-20 2022-05-20 Lightweight solid rocket engine composite construction spray tube device

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202210549573.4A CN115506919A (en) 2022-05-20 2022-05-20 Lightweight solid rocket engine composite construction spray tube device

Publications (1)

Publication Number Publication Date
CN115506919A true CN115506919A (en) 2022-12-23

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ID=84500669

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202210549573.4A Pending CN115506919A (en) 2022-05-20 2022-05-20 Lightweight solid rocket engine composite construction spray tube device

Country Status (1)

Country Link
CN (1) CN115506919A (en)

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